TWO-MODE IGNITOR AND A TWO-MODE METHOD OF INJECTION FOR IGNITING A ROCKET ENGINE

摘要

A two-mode ignitor and to a two-mode method of injection into the ignitor, which includes a feed for a first propellant, a feed for a second propellant, a feed for a high pressure fluid, a first buffer tank, a second buffer tank, a first switch device, a second switch device, and a torch-forming combustion chamber; a downstream orifice from the first buffer tank and a downstream orifice from the second buffer tank both open out into the combustion chamber; the first switch device and second switch device devices are configured respectively to connect an upstream orifice of the first buffer tank with either the first feed or with the feed for high pressure fluid, and to connect the upstream orifice of the second buffer tank either with the second feed or with the feed for the high pressure fluid.

主权项

1. A two-mode ignitor for a rocket engine suitable for operating at low pressure or at high pressure, the ignitor comprising:
a low pressure feed for feeding a first propellant; a low pressure feed for feeding a second propellant; a feed for feeding a high pressure fluid; a first buffer tank; a second buffer tank; a first switch device; a second switch device; and a torch-forming combustion chamber; wherein a downstream orifice from the first buffer tank and a downstream orifice from the second buffer tank both open out into the combustion chamber; wherein the first switch device and the second switch device are configured respectively to connect an upstream orifice of the first buffer tank with either the feed for feeding the first propellant or with the feed for feeding high pressure fluid, and to connect the upstream orifice of the second buffer tank either with the feed for feeding the second propellant or with the feed for feeding the high pressure fluid; and wherein the respective volumes of the first buffer tank and of the second buffer tank are configured so that during high pressure operation the desired flow rates of the first propellant and of the second propellant are maintained for a duration that is sufficient to enable ignition.