An investigation was conducted to determine the feasibility of a low-cost, caseless, solid-fuel integral-rocket ramjet (IRSFRJ) that has no ejecta. Analytical design of a ramjet powered air-to-ground missile capable of being fired from a remotely piloted vehicle or helicopter was accomplished using current JANNAF and Air Force computer codes. The results showed that an IRSFRJ powered missile can exceed the velocity and range of current systems by more than a two to one ratio, without an increase in missile length and weight. A caseless IRSFRJ with a non ejecting port cover was designed and tested. The experimental results of the static tests showed that a low-cost, caseless IRSFRJ with a non-ejectable port cover is a viable design. Rocket ramjet transition was demonstrated and ramjet ignition was found to be insensitive to the booster tail off to air injection timing sequence.
Design and Testing of a Caseless Solid-Fuel Integral-Rocket Ramjet Engine for Use in Small Tactical Missiles
1991
60 pages
Report
Keine Angabe
Englisch
Air & Space-Launched Missiles , Jet & Gas Turbine Engines , Air , Air force , Booster rocket engines , Computer programs , Ejecta , Guided missiles , Helicopters , Ignition , Injection , Integral rocket ramjets , Length , Ramjet engines , Ranges(Facilities) , Ratios , Remotely piloted vehicles , Rocket ramjets , Sequences , Solid fuels , Static tests , Tactical weapons , Tail assemblies , Time , Transitions , Viability , Solid fuel integral rocket ramjets , Air to ground missiles , Theses
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