Increased Combat Radius of Naval Tactical Aircraft

OUSD (R&E) CRITICAL TECHNOLOGY AREA(S): Sustainment OBJECTIVE: Identify, characterize, and validate innovative methods to increase the unrefueled combat radius of Naval tactical aircraft. DESCRIPTION: It is expected that recent technological advances may be leveraged to increase a tactical aircraft's unrefueled combat radius. Aircraft combat radius is a key factor in the ability of the Naval force to deliver long-range fires. The objective of this STTR topic is to identity and quantify innovative concepts to increase the combat radius of a tactical aircraft (Phase I) and then validate the feasibility of the concepts and implement into a prototype(s) (Phase II). Concepts may include but are not limited to: modification to propulsion, fuels, flight controls, drag reduction, weight reduction, fuel storage, or other methods. Concepts may also include non-materiel solutions (i.e., changes to concepts of employment). Key considerations are the anticipated increase in range provided by the concept(s), the expected challenges and costs of developing and integrating the solution(s) into a Naval tactical aircraft, and the suitability of the solution(s) for aircraft carrier operations. The goal is that concepts identified in Phase I will reach Technology Readiness Level (TRL) 3 (analytical proof of concept). The goal is that concepts will reach TRL 4-5 (component and/or breadboard validation in laboratory environment) by the end of Phase II. PHASE I: Conduct a trade study of proposed concepts culminating in low-fidelity quantification of concepts and their potential benefits. Consider integration cost and schedule. The goal is that concepts identified in Phase I will reach Technology Readiness Level (TRL) 3 (analytical proof of concept). Develop plans to validate the concepts at the component level in a laboratory environment (Phase II). PHASE II: Build a prototype solution. Conduct component-level validation in a laboratory environment to demonstrate the feasibility and potential benefit of a concepts. Validation methods could include in-depth computation fluid dynamics (CFD) studies, small-scale wind tunnel validation experiments, or similar methods. The goal is that concepts will reach TRL 4-5 (component and/or breadboard validation in laboratory environment) by the end of Phase II. Deliver a plan for how the concept would be integrated into a tactical aircraft, an estimate of the non-recurring engineering costs, an approximate schedule to IOC, and a risk analysis. PHASE III DUAL USE APPLICATIONS: Mature the concepts to TRL 6, and work with the program office and original equipment manufacturer (OEM) to develop an Engineering Change Proposal (ECP). Concepts developed under this topic will be relevant to commercial transport aircraft and general aviation for the purpose of increasing the efficiency of flight. REFERENCES: 1. Jahanmiri, Mohsen. Aircraft Drag Reduction: An Overview. Research report 2011:02. Division of Dynamics, Department of Applied Mechanics, Chalmers University of Technology, G teborg, Sweden, 2011. https://publications.lib.chalmers.se/records/fulltext/137214.pdf 2. Quadrio M.; Chiarini, A.; Banchetti, J.; Gatti, D.; Memmolo A. and Pirozzoli, S. Drag reduction on a transonic airfoil. Journal of Fluid Mechanics, 2022 ; 942:R2. doi:10.1017/jfm.2022.369 3. Cacciatori, Lorenzo; Brignoli, Carlo; Mele, Benedetto; Gattere, Federica; Monti, Celeste and Quadrio, Maurizio. "Drag Reduction by Riblets on a Commercial UAV." Applied Sciences 12(10), 2022, 5070. https://doi.org/10.3390/app12105070 KEYWORDS: Drag Reduction; Tactical Aircraft; Extended Range; Endurance; Combat Radius; Propulsion Efficiency