초록 ▼

A propulsion system includes a canted multinozzle plate, which has a multitude of small nozzles angled (not perpendicular) to major surfaces of the multinozzle grid plate. The multinozzle plate may be a cylindrical section or plate, and the multitude of nozzles may be substantially axisymmetric abou

A propulsion system includes a canted multinozzle plate, which has a multitude of small nozzles angled (not perpendicular) to major surfaces of the multinozzle grid plate. The multinozzle plate may be a cylindrical section or plate, and the multitude of nozzles may be substantially axisymmetric about the cylindrical plate. The propulsion system includes a pressurized gas source which may be placed either forward or aft of the multinozzle grid plate. The propulsion system may have a conical insert, an internal flow separator cone, to aid in changing directions of flow from the pressurized gas source, to divert the flow through the multiple nozzles.

대표청구항 ▼

What is claimed is: 1. A propulsion system comprising: a pressurized gas source; and a multinozzle grid plate operatively coupled to the pressurized gas source, wherein the multinozzle grid plate is substantially cylindrical, having major surfaces; wherein the multinozzle grid plate has plural conv

What is claimed is: 1. A propulsion system comprising: a pressurized gas source; and a multinozzle grid plate operatively coupled to the pressurized gas source, wherein the multinozzle grid plate is substantially cylindrical, having major surfaces; wherein the multinozzle grid plate has plural convergent-divergent nozzles therein that are canted nozzles, angled relative to the major surfaces of the multinozzle grid plate; wherein the nozzles are in multiple rows longitudinally spaced along the multinozzle grid plate; and wherein pressurized gas from the pressurized gas source is ejected from the nozzles of the multinozzle grid plate. 2. The propulsion system of claim 1, wherein the propulsion system is part of a rocket vehicle. 3. The propulsion system of claim 2, wherein the multinozzle grid plate is located in the rocket vehicle aft of the pressurized gas source. 4. The propulsion system of claim 2, wherein the multinozzle grid plate is located in the rocket vehicle forward of the pressurized gas source. 5. The propulsion system of claim 1, further comprising a flow separator cone within the multinozzle grid plate. 6. The propulsion system of claim 5, wherein the flow separator cone turns flow from the pressurized gas source toward the nozzles. 7. The propulsion system of claim 6, wherein the flow separator cone has a curved surface that turns the flow. 8. The propulsion system of claim 6, wherein a surface of the flow separator cone has an outer edge that is directed in substantially along a direction of the nozzles. 9. The propulsion system of claim 1, wherein the nozzles are substantially axisymmetrically located about the multinozzle grid plate. 10. The propulsion system of claim 1, wherein the nozzles of the multiple rows are axially aligned with one another. 11. The propulsion system of claim 1, wherein the nozzles are substantially flush with an outer major surface of the multinozzle grid plate. 12. The propulsion system of claim 11, wherein the nozzles perform substantially as untruncated nozzles. 13. The propulsion system of claim 2, wherein the cylindrical multinozzle grid plate is a structural member of the rocket vehicle. 14. The propulsion system of claim 1, wherein convergent sections of the nozzles are substantially axisymmetric. 15. The propulsion system of claim 1, wherein the nozzle plate includes at least 100 canted nozzles. 16. A propulsion system comprising: a pressurized gas source; a multinozzle grid plate operatively coupled to the pressurized gas source, wherein the multinozzle grid plate is substantially cylindrical; and a flow separator cone within the multinozzle grid plate; wherein the multinozzle grid plate has plural convergent-divergent nozzles therein that are canted nozzles, angled relative to major surfaces of the multinozzle grid plate; wherein the flow separator cone turns flow from the pressurized gas source toward the nozzles; wherein the nozzles are substantially axisymmetrically located about the multinozzle grid plate; wherein the nozzles are substantially flush with an outer major surface of the multinozzle grid plate; and wherein the nozzle plate includes at least 100 canted nozzles. 17. A method of propelling a rocket vehicle, the method comprising: providing a propulsion system that includes a pressurized gas source, and a cylindrical multinozzle grid plate having at least 100 convergent-divergent nozzles, wherein the nozzles are canted relative to major surfaces of the multinozzle grid plate, and directing gas from the pressurized gas source through the convergent-divergent nozzles, thereby providing thrust for the rocket vehicle. 18. The method of claim 17, wherein the directing includes turning flow from the pressurized gas source using a flow separator cone of the propulsion system that is within the multinozzle grid plate.