Some aspects of propulsion integration issues for ramjet powered missiles a
re outlined in this paper. The benefits of ramjet propulsion in the Mach 2-
4 range over other types of airbreathing propulsion and rocket propulsion a
re well known. Compared with solid rocket motors, ramjet engines offer a mu
ch higher specific impulse and the capability of thrust management, enablin
g longer stand-off ranges and more flexible operation.
An overview of the ramjet engine cycle is given, highlighting engine/intake
matching issues. This is followed by a performance comparison between a ge
neric ramjet and a solid rocket powered missile (the air-to-air configurati
on is examined by way of example in this paper). As well as over all perfor
mance, intake integration and missile steering issues are considered.
A description of a wind tunnel test model, intake design and tunnel testing
is given. The effects of design Mach number and sidewall removal have been
investigated for twin ventral rectangular intake configurations. These tes
ts were aimed at optimising performance at different flight conditions and
improving tolerance to yawed flight. The impact of the alternative intake d
esigns on missile performance is discussed.