https://www.fbo.gov/?s=opportunity&mode=form&id=6663d37fc6f823055fc1f32213afbdf8&tab=core&_cview=1
Program Description: Air Force Research Laboratory, Aerospace Propulsion Division, AFRL/RQH is soliciting technical and cost proposals on the following research effort:
Statement of Objective/Needs: The Aerospace Propulsion Division of Air Force Research Laboratory (AFRL) focuses on high-speed, air-breathing propulsion, including relevant research and development – all directed to raising the standards of national capability and to deliver such technology to the warfighter. Applications may include weapons and Intelligence, Surveillance, and Reconnaissance (ISR).
The program will develop, integrate and demonstrate elements of the technology base for liquid hydrocarbon (HC) fueled scramjet propulsion systems. The focus of this effort is on: (1) improved performance and operability of hydrocarbon scramjets, (2) develop the ability to reliably start a scramjet engine in flight, (3) increase the scale of scramjet engines, and (4) methods for test of medium and large scale hypersonic propulsion systems. This effort fits a broader process of developing high speed propulsion for applications of increasing size and complexity; and, how the proposed approach is adaptable to meet the requirements of various vision vehicles (weapon, ISR platforms).
This effort will be the cornerstone contract in AFRL/RQH to conduct research and development in high speed propulsion. To achieve this end, we are looking for industry partner(s) to research, develop and test innovative design(s) for scramjet engine flowpath component technology development and integration, fuel system technologies and their integration into the engine, high temperature structures and materials, and instrumentation and test facilities/techniques. The engine is expected to operate at high heat load conditions using liquid hydrocarbon fuels, including endothermics where appropriate. Critical technical issues for the combustor are seen as fuel injection (including staging and scheduling across the operating envelope), mixing, flame stabilization and piloting, structural durability, chemical kinetics, and engine cold start. The impact on overall engine performance must be addressed including trading off injector performance, mixing, and flame stabilization with system losses. Suitable figures of merit shall be developed and tracked for component through total engine performance.
Program Description: Air Force Research Laboratory, Aerospace Propulsion Division, AFRL/RQH is soliciting technical and cost proposals on the following research effort:
Statement of Objective/Needs: The Aerospace Propulsion Division of Air Force Research Laboratory (AFRL) focuses on high-speed, air-breathing propulsion, including relevant research and development – all directed to raising the standards of national capability and to deliver such technology to the warfighter. Applications may include weapons and Intelligence, Surveillance, and Reconnaissance (ISR).
The program will develop, integrate and demonstrate elements of the technology base for liquid hydrocarbon (HC) fueled scramjet propulsion systems. The focus of this effort is on: (1) improved performance and operability of hydrocarbon scramjets, (2) develop the ability to reliably start a scramjet engine in flight, (3) increase the scale of scramjet engines, and (4) methods for test of medium and large scale hypersonic propulsion systems. This effort fits a broader process of developing high speed propulsion for applications of increasing size and complexity; and, how the proposed approach is adaptable to meet the requirements of various vision vehicles (weapon, ISR platforms).
This effort will be the cornerstone contract in AFRL/RQH to conduct research and development in high speed propulsion. To achieve this end, we are looking for industry partner(s) to research, develop and test innovative design(s) for scramjet engine flowpath component technology development and integration, fuel system technologies and their integration into the engine, high temperature structures and materials, and instrumentation and test facilities/techniques. The engine is expected to operate at high heat load conditions using liquid hydrocarbon fuels, including endothermics where appropriate. Critical technical issues for the combustor are seen as fuel injection (including staging and scheduling across the operating envelope), mixing, flame stabilization and piloting, structural durability, chemical kinetics, and engine cold start. The impact on overall engine performance must be addressed including trading off injector performance, mixing, and flame stabilization with system losses. Suitable figures of merit shall be developed and tracked for component through total engine performance.
