A spacecraft, reconfigurable from a launch configuration to an on-orbit configuration, the spacecraft comprising: a main body structure; a manipulator; a stack of multiple rigid reflectors; and an attachment arrangement, including at least one hold-down assembly, wherein each hold-down assembly includes an elongate housing and is disposed such that a long axis of the elongate housing is parallel to a first direction, wherein the elongate housing of at least one hold-down assembly is disposed so as to protrude through a respective hole in a surface of at least one reflector; wherein: in the launch configuration, the at least one hold-down assembly is in a fully engaged configuration such that the attachment arrangement mechanically attaches the first reflector with the main body structure so as to prevent relative motion of the first reflector with respect to the spacecraft main body in each of six degrees of freedom; wherein the at least one hold-down assembly is actuatable from the fully engaged configuration to a partially engaged configuration such that the attachment arrangement permits movement of the first reflector in the first direction; the manipulator is configured to: grasp the first reflector; move the first reflector a distance in the first direction sufficient to disengage the first reflector from the attachment arrangement; and move the first reflector, with the manipulator, from a first position proximate to the attachment arrangement to a second position proximate to a deployed position associated with the on-orbit configuration; and when the at least one hold-down assembly is in the partially engaged configuration, the hold-down assembly is configured to prevent translation or rotation of the first reflector other than translation in the first direction. a main body structure; a manipulator; a stack of multiple rigid reflectors; and an attachment arrangement, including at least one hold-down assembly, in the launch configuration, the at least one hold-down assembly is in a fully engaged configuration such that the attachment arrangement mechanically attaches the first reflector with the main body structure so as to prevent relative motion of the first reflector with respect to the spacecraft main body in each of six degrees of freedom; wherein the at least one hold-down assembly is actuatable from the fully engaged configuration to a partially engaged configuration such that the attachment arrangement permits movement of the first reflector in the first direction; the manipulator is configured to: grasp the first reflector; move the first reflector a distance in the first direction sufficient to disengage the first reflector from the attachment arrangement; and move the first reflector, with the manipulator, from a first position proximate to the attachment arrangement to a second position proximate to a deployed position associated with the on-orbit configuration; and when the at least one hold-down assembly is in the partially engaged configuration, the hold-down assembly is configured to prevent translation or rotation of the first reflector other than translation in the first direction. the at least one hold-down assembly is actuatable from the fully engaged configuration to a partially engaged configuration such that the attachment arrangement permits movement of the first reflector in the first direction; the manipulator is configured to: grasp the first reflector; move the first reflector a distance in the first direction sufficient to disengage the first reflector from the attachment arrangement; and move the first reflector, with the manipulator, from a first position proximate to the attachment arrangement to a second position proximate to a deployed position associated with the on-orbit configuration; and when the at least one hold-down assembly is in the partially engaged configuration, the hold-down assembly is configured to prevent translation or rotation of the first reflector other than translation in the first direction. grasp the first reflector; move the first reflector a distance in the first direction sufficient to disengage the first reflector from the attachment arrangement; and move the first reflector, with the manipulator, from a first position proximate to the attachment arrangement to a second position proximate to a deployed position associated with the on-orbit configuration; and when the at least one hold-down assembly is in the partially engaged configuration, the hold-down assembly is configured to prevent translation or rotation of the first reflector other than translation in the first direction.