Abstract: A spacecraft, such as a satellite in geosynchronous orbit, is powered using at least two independently controllable batteries, such as lithium ion batteries, operably connected to the power-consuming components of the spacecraft. Each battery is operable in a higher-temperature range and inactivated in a lower-temperature range. The first battery and the second battery are operated in the higher-temperature range during a first period of time. The first battery is thereafter operated in the higher-temperature range during a second period of time, with the second battery being non-operational and in the lower-temperature range during the second period of time. The first battery and the second battery are thereafter operated in the higher-temperature range during a third period of time. The second battery is thereafter operated in the higher-temperature range during a fourth period of time, with the first battery being non-operational and in the lower-temperature range during the fourth period of time.

Abstract: An apparatus and method for controlling the temperature of a battery used in a spacecraft or an electric vehicle are disclosed. The apparatus includes a thermal conductor, such as a thermally-conductive heat pipe or forced-fluid cooling loop, that is in thermal contact with thermally-conductive cell terminals of the battery, and a heat sink, such as a radiator. The inventive method includes operating the battery to generate and conduct heat to the thermally-conductive battery cell terminals. The generated heat is passed via conduction from the terminals to the thermal conductor. The heat is conducted through the thermal conductor to a heat sink which may be remotely located with respect to the battery. Preferably, the thermal conductor remains electrically insulated from the battery cell terminals and the heat sink.

Abstract: Discrete carrier and lattice structures are bonded together to form a lightweight rigid solar panel. The carrier includes a pair of electrically inert face sheets bonded on opposite sides of a thin thermoconductive honeycomb core. The face sheets provide an electrically inert surface for receiving a solar cell array and the honeycomb core forms a heat sink for conducting heat away from the solar cell array. The lattice includes a pair of patterned face sheets having a high elastic modulus bonded on opposite sides of a lattice base. The patterned face sheets provide axial stiffness and the lattice base separates them to provide bending stiffness. By splitting the solar panel into discrete carrier and lattice components, the present invention reduces the weight of existing solar panels by approximately 40% and increases power efficiency by approximately 10%.

Abstract: A solar cell assembly wherein a solar cell is provided with electrical layer contacts for both the p-type semiconductor layer and the n-type semiconductor layer which are exposed on a top side of the solar cell, so that electrical contact to both layers can be made from the top side of the cell, and a glass cover overlying the solar cell includes a pair of U-shaped electrical cell contacts extending over the sides of the glass cover so that one leg of each U makes contact with one of the layer contacts and the other leg is accessible from the top of the cover glass. External electrical contact to the cell is easily and conveniently made, and cells can be electrically joined to adjacent cells in an array using a connector bar. The glass cover also supports the solar cell so that excess material on the substrate of the solar cell can be etched away to reduce the weight of the solar cell assembly.

Abstract: A solar cell assembly wherein a solar cell is provided with electrical layer contacts for both the p-type semiconductor layer and the n-type semiconductor layer which are exposed on a top side of the solar cell, so that electrical contact to both layers can be made from the top side of the cell, and a glass cover overlying the solar cell includes a pair of U-shaped electrical cell contacts extending over the sides of the glass cover so that one leg of each U makes contact with one of the layer contacts and the other leg is accessible from the top of the cover glass. External electrical contact to the cell is easily and conveniently made, and cells can be electrically joined to adjacent cells in an array using a connector bar. The glass cover also supports the solar cell so that excess material on the substrate of the solar cell can be etched away to reduce the weight of the solar cell assembly.