Missile control system and method

A rocket engine control valve comprising:

• a fixed portion integrated to a pressure chamber and having fixed portion openings therein;
• a movable portion having movable portion openings therein;
• and
• an actuator mechanically coupled to the movable portion, for rotating the movable portion relative to the fixed portion;
• wherein the movable portion overlies the fixed portion;
• wherein the movable portion is rotatably mounted to the fixed portion;
• wherein the fixed portion openings and the movable portion openings combine to produce plural nozzles each having a convergent section, a divergent section, and a throat;
• wherein the fixed portion openings and the movable portion openings line up, allowing flow therethrough, when the movable portion is in an open position relative to the fixed portion;
• wherein the fixed portion openings and the movable portion openings are offset from one another, preventing flow therethrough, when the movable portion is in a closed position relative to the fixed portion;
• wherein the fixed portion is a fixed substantially circular plate;
• wherein the movable portion is a movable substantially circular plate;
• wherein the portions are coupled together at a central axis of the circular plates;
• wherein the actuator includes:
• a motor;
• a threaded shaft;
• and
• a nut on the threaded shaft;
• wherein the nut is fixedly coupled to the movable plate, such that rotation of the shaft causes movement of the movable plate;
• and
• wherein the nut has trunnions that engage holes in a yoke that is attached to the movable plate.

A method of controlling thrust from a rocket engine, the method comprising:

• providing pressurized gas upstream of a control valve;
• and
• relatively configuring portions of the control valve, thereby selectively aligning or not aligning plural holes in each of the portions, to thereby allow or shut off flow through the control valve;
• wherein the holes, when aligned, form plural convergent-divergent nozzles.

A rocket engine control valve comprising:

• a fixed portion integrated to a pressure chamber and having fixed portion openings therein;
• and
• a movable portion having movable portion openings therein;
• wherein the movable portion overlies the fixed portion;
• wherein the movable portion is rotatably mounted to the fixed portion;
• wherein the fixed portion openings and the movable portion openings combine to produce plural nozzles each having a convergent section, a divergent section, and a throat;
• wherein the fixed portion openings and the movable portion openings line up, allowing flow therethrough, when the movable portion is in an open position relative to the fixed portion;
• wherein the fixed portion openings and the movable portion openings are offset from one another, preventing flow therethrough, when the movable portion is in a closed position relative to the fixed portion;
• and
• wherein the control valve also includes one or more fixed nozzles that are maintained open.

A rocket engine control system comprising:

• a pressurized gas source;
• and
• thrusters downstream from the pressurized gas source and receiving flow from the gas source, for controlling thrust in different directions;
• wherein each of the thrusters includes a control valve and an actuator coupled to the control valve for separately actuating the control valve;
• wherein each of the control valves includes:
• a fixed portion integrated to a pressure chamber and having fixed portion openings therein;
• and
• a movable portion having movable portion openings therein;
• wherein the movable portion overlies the fixed portion;
• wherein the movable portion is rotatably mounted to the fixed portion;
• wherein the fixed portion openings and the movable portion openings combine to produce plural nozzles each having a convergent section, a divergent section, and a throat;
• wherein the fixed portion openings and the movable portion openings line up, allowing flow through both the fixed portion openings and the movable portion openings, when the movable portion is in an open position relative to the fixed portion;
• and
• wherein the fixed portion openings and the movable portion openings are offset from one another, preventing flow through the fixed portion openings and preventing flow through the movable portion openings, when the movable portion is in a closed position relative to the fixed portion.

A rocket engine control valve comprising:

• a fixed portion in communication with a pressure chamber and having fixed portion openings therein;
• and
• a movable portion having movable portion openings therein;
• and
• wherein the movable portion overlies the fixed portion;
• wherein the movable portion is rotatably mounted to the fixed portion at an axis of the portions;
• wherein the fixed portion openings and the movable portion openings line up, allowing flow therethrough, when the movable portion is in an open position relative to the fixed portion;
• wherein the fixed portion openings and the movable portion openings are offset from one another, preventing flow therethrough, when the movable portion is in a closed position relative to the fixed portion;
• and
• wherein in moving from the open position to the closed position the fixed portion openings and the movable portion openings offset from one another to prevent flow therethrough first for openings farther from the axis, and later for openings closer to the axis.