Session
Technical Session IV: Launch Vehicles & On-Orbit Operations
Abstract
Under funding from the Naval Research Laboratory (NRL), Rocket Research Company (RRC) has recently completed a one-year study and design effort on the Small Upper Stage (SUS). The goal of this effort was to create a generic, low-cost propulsion stage design capable of being integrated to several different launch vehicles (LV's) and capable of providing a mission enabling orbit transfer function to a variety of different small satellite missions. In order to accomplish this goal, a launch vehicle survey was conducted to establish the current LV capability and environments with respect to small satellites. In addition, a small satellite survey was conducted to establish the orbital needs of the small satellite community. With this information, the SUS specification was created. Based on this specification, the preliminary design of the SUS was developed. This design is capable of being integrated onto several different LV's and is capable of providing the orbit adjust requirements for more than 75 percent of the small satellite missions identified. The SUS design has capabilities of providing small satellites with several orbit transfer maneuvers from a LEO parking orbit (e.g., Hohmann transfer, circularization, plane change and deorbit). The SUS, containing a single or multiple small satellites, can be integrated onto a host LV as a primary on the SLV's, as a secondary on the MLV's or as multiples on a dedicated LV. With the completion of a proposed SUS development and qualification program, the LV and small satellite communities will have a new asset to enhance current capabilities and enable future missions without the need to fund a nonrecurring program for a custom propulsion stage.
Small Upper Stage: An Orbit Enabling Hydrazine Propulsion Stage for the Small Satellite Community
Under funding from the Naval Research Laboratory (NRL), Rocket Research Company (RRC) has recently completed a one-year study and design effort on the Small Upper Stage (SUS). The goal of this effort was to create a generic, low-cost propulsion stage design capable of being integrated to several different launch vehicles (LV's) and capable of providing a mission enabling orbit transfer function to a variety of different small satellite missions. In order to accomplish this goal, a launch vehicle survey was conducted to establish the current LV capability and environments with respect to small satellites. In addition, a small satellite survey was conducted to establish the orbital needs of the small satellite community. With this information, the SUS specification was created. Based on this specification, the preliminary design of the SUS was developed. This design is capable of being integrated onto several different LV's and is capable of providing the orbit adjust requirements for more than 75 percent of the small satellite missions identified. The SUS design has capabilities of providing small satellites with several orbit transfer maneuvers from a LEO parking orbit (e.g., Hohmann transfer, circularization, plane change and deorbit). The SUS, containing a single or multiple small satellites, can be integrated onto a host LV as a primary on the SLV's, as a secondary on the MLV's or as multiples on a dedicated LV. With the completion of a proposed SUS development and qualification program, the LV and small satellite communities will have a new asset to enhance current capabilities and enable future missions without the need to fund a nonrecurring program for a custom propulsion stage.
