Abstract: A constrained solar array (24) for a satellite (20) and method for making the same are disclosed. The solar array (24) includes a superstructure (30) with solar cells (80) mounted thereon to provide power to a main satellite body (22) and instruments mounted thereon. A flexible tensile member (40) extends relative to the superstructure (30) and is placed under tension to place the solar array (24) in a constrained condition which reduces thermal transients in and increases the bending frequency of the solar array (24). Preferably, a pair of support arms (34,36) are cantilevered from the superstructure (30). The flexible tensile member (40) pulls upon the support arms (34,36) to apply bending moments to the superstructure (30) to maintain the solar array (24) in a distorted shape.

Abstract: A rigid panel solar array for a spacecraft. The layers of materials for the panels are selected and oriented to control the net coefficient of thermal expansion in the array's longitudinal direction. Some of the layers are discontinuous and softly coupled to the others by flexible adhesive materials. The panels are interconnected with hinge members which are positioned at appropriate locations and with appropriate degrees of freedom so that thermally induced transverse bending does not cause transverse motion of the center-of-mass of the panels.