Hypergolic hybrid motor igniter
AssigneeThe Aerospace Corporation
InventorsBrian Blaise Brady, John D. Desain
Life of this patent
Estimating the term…
Abstract
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.
Claims20
An apparatus, comprising:
- hypergolic fuel grains configured to form a chamber;
- and
- an oxidizer valve configured to allow a pressurized oxidizer to enter the chamber, wherein the hypergolic fuel grains are configured to cause an ignition of a larger rocket motor upon contact with the pressurized oxidizer.
An apparatus, comprising:
- a first rocket motor comprising hypergolic fuel grains;
- and
- a second rocket motor operatively connected to the first rocket motor, wherein the first rocket motor is configured to ignite, and reignite at a later time, the second rocket motor.
A hybrid rocket motor, comprising:
- hypergolic fuel grains configured to form a chamber and operatively connected to a chamber of a larger rocket motor,
- wherein the hypergolic fuel grains are configured to ignite the larger rocket motor when a pressurized oxidizer is released into the chamber formed by the hypergolic fuel grains.
Dependencies are inferred from the claim text.