During the proposed Phase II research and development effort, the project team will integrate previously demonstrated technologies into a low-cost transfer stage based on a high energy density, aluminized, green monopropellant. The resulting stage will achieve the Mass Fraction and Specific Impulse performance needed to send small-spacecraft payloads in the near term to the cislunar environment, with longer term potential for farther destinations such as near-Earth objects, Mars, or Venus. The stage will be designed to provide support services to the spacecraft post-deployment, such as communications relay or positioning, navigation, and timing (PNT) services. The Phase I program will conclude with a hot-fire demonstration of the propulsion system.
Small spacecraft transfer stage/upper stage propulsion systems for Small Launch Vehicles
Low cost space lift, exploration missions to the moon and Mars