When I worked on the Hawk motor design at Aerojet in 1957, that was
apparently a great leap forward in propulsion. (Navy signed Aerojet up
to build the dual-thrust Tartar motor based on the same design.)
I wonder now if Hawk was the first to develop this dual-propellant
concept? Where was it used before 1957?
And something I do not get to this day, is how is the nozzle throat
area configured? If it is optimum for the ~5-sec boost phase, the
~20-sec sustainer phase would necessarily be way off optimum, no?
And if the sustainer runs at nearly optimum At and Pc, how does that
affect the boost burn?
Anyone help me get that trade-off for the Hawk and Tartar type solid motors?
Edward