A solar array structure for a spacecraft includes one or a pair of flexible blanket or other foldable solar arrays and a deployable frame structure. The deployable frame structure includes a T-shaped yoke structure, a T-shaped end structure, and one or more rigid beams, the T-shaped yoke structure connectable to the spacecraft. When deployed, the frame structure tensions the flexible blanket solar array or arrays between the T-shaped yoke structure and the T-shaped end structure. When stowed, the flexible blanket solar array or arrays are folded in an accordion manner to form a stowed pack or packs between the cross-member arms of the T-shaped yoke structure and the T-shaped end structure, also stowed in its own Z-fold arrangement. The cross-member arms of the T-shaped end structure can include a solar array that can provide power before deployment while the flexible blanket solar array is stowed.

A solar array structure for a spacecraft includes one or a pair of flexible blanket or other foldable solar arrays (such as flexible panels) and a deployable frame structure. The deployable frame structure includes a T-shaped yoke structure, a T-shaped end structure, and one or more rigid beams, the T-shaped yoke structure connectable to the spacecraft. When deployed, the frame structure tensions the flexible blanket solar array or arrays between the T-shaped yoke structure and the T-shaped end structure. When stowed, the flexible blanket solar array or arrays are folded in an accordion manner to form a stowed pack or packs between the cross-member arms of the T-shaped yoke structure and the T-shaped end structure, also stowed in its own Z-fold arrangement. The cross-member arms of the T-shaped end structure can include a solar array that can provide power before deployment while the flexible blanket solar array is stowed.

A solar array structure for a spacecraft includes one or a pair of flexible blanket or other foldable solar arrays and a deployable frame structure. The deployable frame structure includes a T-shaped yoke structure, a T-shaped end structure, and one or more rigid beams, the T-shaped yoke structure connectable to the spacecraft. When deployed, the frame structure tensions the flexible blanket solar array or arrays between the T-shaped yoke structure and the T-shaped end structure. When stowed, the flexible blanket solar array or arrays are folded in an accordion manner to form a stowed pack or packs between the cross-member arms of the T-shaped yoke structure and the T-shaped end structure, also stowed in its own Z-fold arrangement. The cross-member arms of the T-shaped end structure can include a solar array that can provide power before deployment while the flexible blanket solar array is stowed.

A deployable device includes a supporting structure, a mandrel able to move in rotation with respect to the supporting structure about a first axis Z, a membrane able to pass from a rolled-up configuration rolled up around the mandrel about the first axis Z to a deployed configuration deployed along a second axis X substantially perpendicular to the first axis Z. The device comprises two fittings secured to the mandrel at their centre, arranged one on either side of the membrane and comprising first stubs on their periphery, a casing extending between the two fittings, the casing comprising second stubs of a shape complementing the shape of the first stubs, the casing being able to pass from a rolled-up configuration at least partially enveloping the membrane in the rolled-up configuration to a deployed configuration at least partially superposed on the membrane in the deployed configuration.

Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example launch vehicle includes a first space vehicle including a first core structure and a first electric propulsion system, and a second space vehicle including a second core structure and a second electric propulsion system, the second core structure releasably attached to the first space vehicle in a stacked configuration.

A solar power generator includes a support, a plurality of first electrodes disposed on one side of the support, a solar cell module mounted to the support, and a plurality of second electrodes disposed on the opposite side of the support. The solar cell module is electrically connected to a pair of the first electrodes via a transmission line for module connection. Three pairs of the second electrodes are electrically connected one-to-one to three pairs of the first electrodes via a transmission line for passage of current. Three of the second electrodes are electrically connected to one of the first electrode via the transmission line for passage of current.

A solar power generator includes a support, a plurality of first electrodes disposed on one side of the support, a solar cell module mounted to the support, and a plurality of second electrodes disposed on the opposite side of the support. The solar cell module is electrically connected to a pair of the first electrodes via a transmission line for module connection. Three pairs of the second electrodes are electrically connected one-to-one to three pairs of the first electrodes via a transmission line for passage of current. Three of the second electrodes are electrically connected to one of the first electrode via the transmission line for passage of current.

Solar radiation is collected and converted to microwave energy by means maintained in outer space on one or more platforms in space. The microwave energy is then transmitted to earth and directed to and constantly focused on one or more segments of a generally circular and slowly rotating tropical depression, which is a precursor to a tropical storm and then a hurricane (alternatively called a cyclone or typhoon). The focused microwave energy interrupts the cycle of vertical upward and downward movement of air, water, & water vapor, and destabilizes the developing rotational motion of the tropical depression, causing it to break up and dissipate, and preventing it from ultimately developing into a hurricane. When not focusing microwave energy on a tropical depression, the microwave energy can alternatively be used to create earth based solar energy, which would help alleviate costs of operating the system solely for hurricane prevention.

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.

An item to write on a surface of a celestial body that has less atmosphere than Earth is received at a communications station and from a user device. An instruction that triggers the robot to write the item on the surface of the celestial body is provided by the communications station and to a robot on the surface of the celestial body. An image of the item written on the surface of the celestial body is received by the communications station and from the robot. The image of the item written on the surface of the celestial body is provided by the communications station and to the user device.