Solar array (15) has a longitudinal axis. Array (15) consists of rigid solar panel members (14,16,18,20) connected together in series along the longitudinal axis. Pairs of hinge members (30,32) are positioned between and connect together each of the panel members (14,16,18,20). Hinge members (30,32) are symmetrically positioned substantially at one-half of the cubed root of the width of the panel members. The movement of the centre of mass of the solar panel members (14,16,18,20) in a direction transverse to the longitudinal axis during thermal induced transverse bending of the panel members (14,16,18,20) is substantially minimised. One of the hinge members (30,32) has transverse and rotational degrees of freedom, while the other (32) of the hinge members has at least a rotational degree of freedom.    USE -   Solar array for satellites that is designed to cause minimal disturbance to their hose spacecraft as the spacecraft passes through the transition zone between lightness and darkness.    ADVANTAGE -   Spacecraft disturbance due to the coefficient of thermal expansion of the array in the transverse direction are rendered negligible. It reduces solar thermal snap effects in rigid solar arrays operating in low earth orbit environments. This allows use of rigid array technology on low earth orbit spacecraft that have tighter pointing requirements, taking advantage of their simple and proven deployment mechanisms. This results in lower cost and a more reliable system than one using more complex flexible array technology. The tighter cell packing density provides lower environmental torques on the spacecraft. Rigid panel solar arrays possess higher flex mode frequencies that lead to less interaction with the spacecraft attitude control system. A more robust, navigation and control system design is allowed for the spacecraft. The effect of transverse expansion is minimised with the placement of the hinges. The thermal expansion coefficient in a longitudinal direction is min