OUSD (R&E) MODERNIZATION PRIORITY: General Warfighting Requirements (GWR) TECHNOLOGY AREA(S): Electronics; Space Platform; Air Platform OBJECTIVE: This topic seeks to preform high speed separation analysis, concept exploration, test and evaluation using sub-scale experiments to enable air-drop of cargo ejected from a rocket that is capable of transporting up to 100 tons of cargo. DESCRIPTION: The Department of the Air Force is exploring rocket transportation capability for DoD logistics and the Air Force Research Laboratory (AFRL) is currently assessing emerging rocket capability across the commercial vendor base, and its potential use for quickly transporting DoD materiel to ports across the globe. The U.S. commercial launch market is building the largest rockets ever, at the lowest prices per pound ever, with second-stages that will reenter the atmosphere and be reused. These advances in the U.S. commercial launch market are presenting the need for assessment and maturation of air-drop cargo concepts where cargo is ejected from the rocket and delivered to a specific destination. Air-drop of cargo is desirable when a rocket cannot land and be unloaded, such as on the ocean or in austere environments where landing on a surface impossible. Air-drop of cargo may be required in an area just after a natural disaster or to remote Forces when landing a rocket is not desired. The goal of this effort is to support the analysis in determining if air-drop of large payloads is feasible and at what speeds. Various concepts of operations (CONOPS) need to be analyzed that include slow drop speeds (< 0.5 Mach) when the rocket is preforming a slow-down maneuver all the way up to fast drop conditions where the rocket is traveling at speeds up to Mach 5. An objective of this effort is to explore multiple CONOPS and preform modeling and simulation using techniques as Computational Fluid Dynamics (CFD) and 6 Degrees of Freed (6DoF) models of the rocket cargo platform. Sub-scale experiments of the ejection mechanisms with the cargo containers is desired in order to get a better understanding of the trade space. Part of the focus of this topic should be on what are the package/container sizes and how many may be needed to make the air-drop mission relevant? What is the range of viable high-speed separation conditions? (Rocket orientation, speed, altitude, ejection technique). What trajectories allow egress of the rocket after air-drop? What are the remaining capabilities of the rocket after air-drop delivery of the intended cargo? Quantification of the parent response to child separation and ejection velocity required for safe separation are part of the analysis on this topic. The main deliverables will be modeling and simulation (M&S) and sub-scale experiments examining the feasibility of air-dropping cargo from a rocket. PHASE I: This topic is intended for technology proven ready to move directly into Phase II. Therefore, a Phase I award is not required. The offeror is required to provide detail and documentation in the Direct to Phase II proposal which demonstrates accomplishment of a Phase I-like effort, including a feasibility study. This includes determining, insofar as possible, the scientific and technical merit and feasibility of ideas appearing to have commercial potential. It must have validated the product-market fit between the proposed solution and a potential AF stakeholder. The offeror should have defined a clear, immediately actionable plan with the proposed solution and the AF customer. Relevant areas of demonstrated experience and success include: M&S, commercial container design or use, ejection systems, parachute delivery systems, concept development, concept demonstration and concept evaluation and sub-scale laboratory experimentation. Phase I type efforts include modeling and simulation using CFD techniques, the ability to create 6DoF models of various rocket designs, concepts and/or prototypes of ejection systems, drogue chute and/or Inflatable Aerodynamic Decelerator (IAD) familiarity, trade-space analysis tools and applications and sub-scale experimentation expertise. The result of Phase 1 type efforts is to assess and demonstrate whether commercial rockets and associated systems can air-drop cargo. PHASE II: Eligibility for a Direct to Phase Two (D2P2) is predicated on the offeror having performed a Phase I-like effort predominantly separate from the SBIR/STTR Programs. These efforts will include M&S, simulation of prototype concepts, sub-scale experimentation, cost benefit analysis, system-of-systems studies, software application and tool development of concepts that enable air-drop of DoD material to any point across the globe. Prototypes, applications, M&S and sub-scale experimentation should explore a wide range of concepts that can be used for air-drop of cargo from commercial rocket capabilities. Concepts should consider areas that are unique to military logistics such as the air-drop of Humanitarian relief supplies, medical equipment and supplies, munitions, fuel and electronic systems. Phase II efforts shall conduct analysis, M&S and sub-scale experimentation to address military-unique requirements that may not be otherwise met by commercial systems used during air-drop type missions. No funding will be invested in developing commercial rocket systems. PHASE III DUAL USE APPLICATIONS: Phase III shall include upgrades to the analysis, M&S, applications, tools and sub-scale experimentation and provide mature prototypes of system concepts. Phase III shall provide a business plan and address the ability to transition technology and system concepts to commercial applications. The adapted non-Defense commercial solutions shall provide expanded mission capability for a broad range of potential Governmental and civilian users and alternate mission applications. Integration and other technical support to operational users may be required. REFERENCES: R. Johnson, Ejection Seat Mechanism in Civil Aircraft , International Journal of Scientific & Engineering Research, Volume 3, Issue 10, October-2012; F. Liu, Review on Ejector Efficiencies in Various Ejector Systems , International Refrigeration and Air Conditioning, 2014; K. Dutt, Analytical Description Of Pneumatic System , International Journal of Scientific & Engineering Research, Volume 4, Issue 9, September-2013; C. Hohmann, B., Tipton, Jr., M. Dutton, Propellant for the NASA Standard Initiator, October 2000, NASA/TP-2000-210186; M. Falbo, R. Robinson, Apollo Experience Report - Spacecraft Pyrotechnic Systems , March 1973, NASA TN D-7141; D. Waye, Design and performance of a parachute for the recovery of a 760-lb payload , Apr 1991, SAND-90-2158C; CONF-9104171-3, ON: DE91007509; J. Hagen, M. Burlone, K. Rojdev, Major Design Choices and Challenges that Enabled the Success of the Ejectable Data Recorder System , March 2020, IEEE Aerospace Conference in March 2020; KEYWORDS: High Speed Ejection Systems; Commercial Cargo Containers; Shock and Vibration Isolation; Computational Fluid Dynamics (CFD); 6 Degrees of Freed (6DoF) models; Modeling and Simulation; Sub-Scale Experimentation; Concept of Operations (CONOPS); High-Speed S
