The conditions under which a ram rocket is superior to a rocket as a power plant for the cruising phase of high altitude supersonic missiles are analyzed and defined. The influence of mission and power plant parameters on the payload of both kinds of engine units is investigated. The advantages of a booster-ram rocket combination over a two-stage rocket are pointed out. This advantage can be increased if the booster acceleration is terminated before the cruise velocity is reached and the ram rocket then continues the acceleration. In that case, the payload attains a maximum at a particular final booster velocity. The working regimes in the ram rocket combustion chamber needed to obtain these optimal conditions are deduced.
The Use of Ram Rockets for High Altitude Missiles
1978
72 pages
Report
Keine Angabe
Englisch
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