A multiple space vehicle launch system (10) that may be adapted to be disposed within a payload region (20) of a launch vehicle fairing (14). The launch system (10) may include a first space vehicle (16), and a second space vehicle (18) releasably attached to the first space vehicle (16) and oriented relative to the first space vehicle (16) such that, when placed within the fairing (14), a launch load of the first space vehicle (16) is transmitted to and borne by the second space vehicle (18). In certain embodiments, the first and second space vehicles (16, 18) each may include one of an electrical propulsion unit (40) and a hybrid chemical and electrical propulsion unit (42). Use of electrical or hybrid chemical and electrical propulsion units (40, 42) enables the second space vehicle (18) to bear all or a significant portion of the launch load of the first space vehicle (16), thereby eliminating the need for additional support structure.