ALTITUDE START CAPABILITY OF EXISTING LARGE LIQUID PROPELLANT ROCKET ENGINES

The application of existing Rocketdyne engines to second stage vehicle applications is examined with respect to potential engine start problems associated with the low ambient pressure of high altitude. It is shown by analytical means and, where necessary, full scale test results that existing booster engines as used in the Saturn vehicle and late model Atlas missiles are directly applicable to such use. It is also shown that, with minor modification, earlier model engines as used in the Thor and Jupiter missiles are adaptable to second stage applications.