REQUEST FOR INFORMATION: Solutions to Enhance US Rocket-Based Combined Cycle (RBCC) Propulsion Technologies

response to this RFI; all costs associated with responding to this RFI will be solely at the interested party's expense. The Government does not intend to award a contract on the basis of this request or to otherwise pay for the information solicited. While the Government intends to use this information for future acquisition planning purposes, it will not release any information about your approach that might in any way compromise your competitive posture or proprietary information. All information received in response to this RFI shall be safeguarded adequately from unauthorized disclosure. All information received in response to this RFI that is marked PROPRIETARY will be handled accordingly. The Government will not be liable for or suffer any consequential damages for any proprietary information not properly identified. Proprietary information will be safeguarded in accordance with the applicable Government regulations. Responses to this RFI will not be returned. Respondents will not be notified of the result of the review. Failure to respond to this RFI does not preclude participation in any future associated request for proposal or white papers that may be issued. Information provided in no way binds the Government to solicit or award a contract. If a solicitation is released, it will be synopsized on the SAM.gov. It is the potential vendor's responsibility to monitor this site for the release of any follow-on information. HOW TO RESPOND: Interested parties shall respond with solutions that meet all or a subset of the aforementioned attributes. Written responses should target maximum of five (5) pages in length for each of the Responsive Scenarios included in the RFI. Using Microsoft Word, 11 point font for a not to exceed total of 10 pages for the response. Responses can be for any or all areas of interest included in this RFI. Administrative information is not included in this page count limitation. All responses shall included the following information: 1. Company Name 2. Business Size for subject NAICS 3. Cage Code/SAM UEI Responses will also include administrative information and shall include the following as a minimum: organization name, address, and name and e-mail of designated point of contact. Respondents should submit, at a minimum, their qualifications and any other information considered pertinent to the requirement to the Contracting Officer no later than 30 days after the publication date of this notice. Information considered to be relevant to this RFI should be sent electronically to: Primary: Alessandra Barzaghi-Martin, Contracing Officer AFTC/PZR alessandra.barzaghi-martin@us.af.mil Secondary: Mathew Pierson, Contracting Officer AFTC/PZRA mathew.pierson@us.af.mil DETAILS The Air Force Research Laboratory�s Rocket and Space Propulsion Division at the AFRL Rocket Laboratory, Edwards AFB, is soliciting information and comments from industry on their ability to identify specific investments in US technology development and demonstration of Rocket-Based Combined Cycle (RBCC) propulsion with application to high-speed systems. As such, the goal of this RFI is to identify current technologies, US industry base, and government subject matter expertise and test facilities that industry could leverage, as well as technology areas requiring further investment. AFRL is particularly interested in developing and leveraging Rotating Detonation Rocket Engine (RDRE) technologies operating with storable propellants, particularly High Test Peroxide (HTP) or any other appropriate liquid non-cryogenic oxidizer that meets the constraints described below, in combination with Rocket Propellant (RP) or Jet Fuel. RDREs offer several advantages over traditional rocket engines in terms of operability, size, and performance, thereby having potential to result in an RBCC performance boost. For the purposes of this RFI, AFRL is interested in RBCC technologies that address the following aspects: Minimize weight: The weight of the RBCC system for a given thrust class is key in enabling missions and shall be minimized. For the purposes of this RFI � turbine based combined cycles (TBCC) are not considered. Maximize scalability: The envisioned RBCC system shall be affordable and mass producible. For the purposes of this RFI - RBCC systems requiring extensive sustainment, logistics, and supply chain, or extensive amounts of exotic materials and exquisite manufacturing techniques, are not considered. Maximize mission utility: Useful missions further require propulsion systems to be fueled and fielded for long periods prior to activation. For the purposes of this RFI � cryogenic propellants are not considered. Maximize propulsion-airframe integration: The RBCC propulsion system outer mold line shall be minimized for a given thrust class. Minimize logistics: The RBCC system shall be operationally sustainable, storable, transportable, integrable, and shall minimize propellant logistics, propellant supply chain risks, and propellant safety requirements for handling in austere environments. This may involve having a common fuel for the rocket propulsion system and the air-breathing propulsion system. Candidate RBCC solutions shall: Incorporate a liquid storable rotating detonation rocket engine (RDRE) as the primary rocket combustor. Support ignition, throttling, and relight at relevant RBCC flight conditions. Support RBCC mission-relevant burn times and therefore have appropriate thermal management subsystems for prolonged operations. Operate with a dedicated liquid storable oxidizer that minimizes logistics. Have a viable path to RBCC demonstration in relevant flight conditions, including flight-testing the RBCC system at relevant velocities, altitudes, and downrange (TRL-6). Maximize operational range: Utilization of RBCC across a broad range of relevant flight conditions requires integration of a robust air inlet and flowpath to enable multi-Mach operability, with smooth mode transitions and to prevent inlet unstart. Maximize compactness and minimize complexity: The design and manufacturing of the air inlet and flowpath shall be compact and minimize complexity in order to maximize RBCC system scalability (i.e., affordability and mass-producibility). Following ignition, acceleration, and attainment of appropriate cruise conditions, the primary RBCC thrust shall be delivered by the air-breathing propulsion system, with the rocket propulsion system providing supplemental performance through ejector and/or rocket-burn augmentation effects. INFORMATION REQUESTED: The Government is contemplating executing development and demonstration activities to enhance US RBCC propulsion technologies. This RFI is seeking input from industry on the following RBCC areas of interest: Identify overall RBCC system characteristics: Identify RBCC flowpaths that would best couple an RDRE with an air-breathing propulsion system. Consider the role and performance of the RDRE and air-breathing propulsion systems when operating concurrently in the air flowpath, including the expected maximum operating speed of the propulsion system, and the approximate inlet conditions for mode transition from RDRE to air-breathing propulsion. Identify potential thermal management solutions to support the desired operating characteristics. Identify RBCC size, weight and power considerations associated with feeding, regu