A multiple space vehicle launch system, comprising: a fairing of a launch vehicle; a first space vehicle; a second space vehicle releasably attached to the first space vehicle and oriented relative to the first space vehicle such that when the first and second space vehicles are oriented in a stacked manner and placed within a payload region of the fairing, a launch load from the first space vehicle is transmitted to and borne by the second space vehicle; and characterised in that the fairing is shaped to enclose the first and the second space vehicles (16, 18), said fairing including a base shaped to support the second space vehicle, wherein the second space vehicle rests upon the base which is part of the fairing, and in that the first space vehicle includes a first electrical propulsion unit as the source of propulsion for the first space vehicle and in that the second space vehicle includes a second electrical propulsion unit as the source of propulsion for the second space vehicle, wherein the first space vehicle includes a first core structure and the second space vehicle includes a second core structure, wherein the first core structure engages with and is attached to the second core structure, and wherein the launch load from the first space vehicle is transmitted to the second space vehicle through the first core structure and the second core structure, and wherein the first core structure is cylindrical and hollow, wherein the second core structure is cylindrical and hollow; wherein the first electrical propulsion unit consists of an ion/plasma motor that utilizes Xenon gas as a propellant that is stored in a first tank located within the first core structure; and the second electrical propulsion unit consists of an ion/plasma motor that utilizes Xenon gas as a propellant that is stored in a second tank located within the second core structure; wherein the first space vehicle includes a first shear load panel mounted on the first core structure and a deployable solar array supported by the first shear load panel, and wherein the second space vehicle includes a second shear load panel mounted on the second core structure and a second deployable solar array supported by the second shear load panel. a fairing of a launch vehicle; a first space vehicle; a second space vehicle releasably attached to the first space vehicle and oriented relative to the first space vehicle such that when the first and second space vehicles are oriented in a stacked manner and placed within a payload region of the fairing, a launch load from the first space vehicle is transmitted to and borne by the second space vehicle; and characterised in that the fairing is shaped to enclose the first and the second space vehicles (16, 18), said fairing including a base shaped to support the second space vehicle, wherein the second space vehicle rests upon the base which is part of the fairing, and in that the first space vehicle includes a first electrical propulsion unit as the source of propulsion for the first space vehicle and in that the second space vehicle includes a second electrical propulsion unit as the source of propulsion for the second space vehicle, wherein the first space vehicle includes a first core structure and the second space vehicle includes a second core structure, wherein the first core structure engages with and is attached to the second core structure, and wherein the launch load from the first space vehicle is transmitted to the second space vehicle through the first core structure and the second core structure, and wherein the first core structure is cylindrical and hollow, wherein the second core structure is cylindrical and hollow; wherein the first electrical propulsion unit consists of an ion/plasma motor that utilizes Xenon gas as a propellant that is stored in a first tank located within the first core structure; and the second electrical propulsion unit consists of an ion/plasma motor that utilizes Xenon gas as a propellant that is stored in a second tank located within the second core structure; wherein the first space vehicle includes a first shear load panel mounted on the first core structure and a deployable solar array supported by the first shear load panel, and wherein the second space vehicle includes a second shear load panel mounted on the second core structure and a second deployable solar array supported by the second shear load panel.