Fig. 11. Blanket element construction (with solar cells). are calculated for the worst-case and expressed in terms of equivalent pressure for comparison purpose. The load due to the gravity gradient is shown only for the blanket surface, and for the total system including a circumferential frame it is one order higher than that shown in the figure. The magnitude of the control force to keep the array surface normal to the sun is required to be of the same order as these external loads. Other loads, for example, the load due to the electromagnetic induction, etc., are neglected. Blanket Figure 11 shows design details of an element of a blanket. The shape of the element is the parallelogram having a corner angle of about 84°. A Kapton base film is stiffened by a thin layer of CFRP border frames, and hinge structures are also formed within the frames as shown in the figure. Because of its particular geometry, the kinematics of the deployment of a 2-D array is entirely different from the conventional deployable array. For instance, as shown in Fig. 12, paths of vertices and thus the envelopes of a blanket depend on the eigen-direction of the 2-D surface, the shape of the boundary, and the initial position of the packaged array. The pattern shown in the left side of the figures indicates symbolically the eigen-direction and the initial position. 4. EXPERIMENT ON BOARD A SPACE FLYER UNIT Deployment Test The array deployment test will be carried out to confirm, mainly, the possibility in
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