The severe temperatures encountered in aircraft at speeds above Mach 3 have created a need for highly efficient use of the fuel supply on board the aircraft as a heat sink for the cooling system. Since the fuel temperature limitations and heat rejection characteristics of the present fixed displacement fuel pumps represent inefficiencies in the system, the use of higher efficiency variable displacement piston type fuel pumps is analyzed. The design of such a pump is shown to be practical and within the present state of the art. It is shown that the effect of the change on the fuel control system is moderate and requires no new or untried techniques.
