Session
Technical Session VII: Launch Vehicles
Abstract
At the present time, small satellite programs are faced with the dilemma that they are sometimes so small that they cannot afford the expense of a dedicated Expendable Launch Vehicle (ELV) and. therefore, must attempt to find a way to get into orbit as a secondary payload. This paper discusses another alternative, the use of a Titan II as a dedicated launch vehicle for a group of small satellites. Launches could be scheduled on a periodic basis as a function of predicted need. The Titan II has the capability of inserting total payload weight of 3,000 to 4,000 lbs. into high-inclination, low-earth orbits and smaller payloads to higher orbits. Orbit changes are possible depending on the altitudes and payloads weights involved. Payload fairings are available for small and large payloads. Since the total payload could conceivably consist of satellites from several unrelated programs, some type of mission "broker" or central contracting agency would be needed to develop and implement a multisatellite mission. This paper offers an approach to implementing a mission of this type that would allow small satellites to schedule a launch on the T-II multisatellite carrier at a predetermined launch date during each year. The costs would be shared between payloads on the basis of weight and volume. This gives those small satellite programs a launch option that would provide on-orbit operation at a predetermined time.
Titan II Small Multisatellite Mission Approach
At the present time, small satellite programs are faced with the dilemma that they are sometimes so small that they cannot afford the expense of a dedicated Expendable Launch Vehicle (ELV) and. therefore, must attempt to find a way to get into orbit as a secondary payload. This paper discusses another alternative, the use of a Titan II as a dedicated launch vehicle for a group of small satellites. Launches could be scheduled on a periodic basis as a function of predicted need. The Titan II has the capability of inserting total payload weight of 3,000 to 4,000 lbs. into high-inclination, low-earth orbits and smaller payloads to higher orbits. Orbit changes are possible depending on the altitudes and payloads weights involved. Payload fairings are available for small and large payloads. Since the total payload could conceivably consist of satellites from several unrelated programs, some type of mission "broker" or central contracting agency would be needed to develop and implement a multisatellite mission. This paper offers an approach to implementing a mission of this type that would allow small satellites to schedule a launch on the T-II multisatellite carrier at a predetermined launch date during each year. The costs would be shared between payloads on the basis of weight and volume. This gives those small satellite programs a launch option that would provide on-orbit operation at a predetermined time.
