Hypergolic hybrid motor igniter

摘要

An apparatus for igniting a larger rocket motor is provided. The apparatus may be a smaller rocket motor that can be ignited hypergolically, when a pressurized oxidizer contacts hypergolic fuel grains of the smaller rocket motor. The hypergolic ignition causes the larger rocket motor to be ignited. The hypergolic ignition of the smaller rocket motor may be stopped after the larger rocket motor is ignited, and the remaining hypergolic fuel grains and the pressurized oxidizer can be reserved for reigniting the larger rocket motor at a later time.

主权项

1. An apparatus, comprising:
hypergolic fuel grains configured to form a chamber coupled to a first inlet of a pre-combustion chamber of a larger rocket motor; an oxidizer valve configured to allow a pressurized oxidizer to enter the chamber, and upon contact with the hypergolic fuel grains, burn the hypergolic fuel grains to generate a flame in the pre-combustion chamber; and an injector configured to inject the pressurized oxidizer through a second inlet of the pre-combustion chamber; wherein the hypergolic fuel grains are configured to cause an ignition of the larger rocket motor upon contact with the pressurized oxidizer by mixing the flame with the pressurized oxidizer injected by the injector through the second inlet, and when the oxidizer valve is closed, the pressurized oxidizer is prevented from entering the chamber and the hypergolic fuel grains are extinguished from burning.