Rapid Turn-Around Flight Testing of a Next-Generation Prototype RNLV (Preprint)

Abstract : This paper presents the status and results from an ongoing development and flight test program that is investigating both reusable nanosat launch vehicles (RNLV), with an emphasis on fast turn-around operations, and early pathfinding for operationally responsive space. A related objective is enhancing the Technology Readiness Level of candidate launch vehicle technologies whenever they can be accommodated as complementary research experiments. The present program builds upon previous work that featured four flight tests (two conducted in a single day within 3.5 hours) with an earlier prototype RNLV first stage (the Prospector 7) that was developed under a Phase I SBIR sponsored by the Air Force Research Laboratory - Propulsion Directorate with support from the Air Force Space & Missile Systems Center. Recent work that falls under the scope of a follow-on Phase II SBIR contract has focused on developing a next-generation prototype RNLV first stage. The Phase II objective is to improve both the performance environment and operational fidelity of these flight tests, thereby bringing them closer to those anticipated for orbital missions. Milestones during the past two years have included horizontal static fire testing of a new 4.5 klbf-thrust LOX/ethanol first stage engine, vertical static fire testing of this engine with an interim test vehicle (the Prospector 8) and its initial flight demonstration, and integration and an initial static fire test attempt with the next prototype vehicle (the Prospector 9). Among the latter's most notable design features are two full-scale composite cryogenic propellant tanks. Final integration and operational preparations are gearing up to initiate low-altitude flight testing later this summer.