This paper describes the facility test equipment and techniques that have been developed for efficient integral rocket-to-ramjet transition testing. The facility and test procedures were demonstrated successfully with the use of representative advanced cruise missile test hardware and test conditions to establish the feasibility of the highperformance center-loaded duct propulsion concept. This concept requires the ramjet flameholder and fuel injectors to be stationed between two solid-propellant rocket grains. The transition test method was selected because it produces the true thermal/time history for both the test hardware and the environment. The test series included component checkout tests, ramburner firings to establish baseline performance, simulated transition tests to verify facility operation, and full rocket-to-ramjet transition firing for design verification.
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