Apparatus to reduce thrust oscillations in a launch vehicle

• US 8,350,199 B2
• Filed: 01/13/2009
• Issued: 01/08/2013
• Est. Priority Date: 01/13/2009
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Kibens, Valdis, Whalen, Edward Andrew
• Primary Examiner(s): Dinh, Tien
• Assistant Examiner(s): KREINER, MICHAEL B
• Application Number:
  US12/352,811
• Publication Number:
  US 20100176247A1
• Time in Patent Office: 1,456 Days
• Field of Search: 244/3.1, 244/3.21, 244/3.22, 244/62, 244/63, 244/158.1, 244/171.1, 244/171.3, 602/53, 602/54, 102/202, 102/286, 102/287, 102/291
• US Class Current: 244/3.1
• CPC Class Codes: B64G 1/002 Launch systems
• CPC Class Codes: B64G 1/403 Solid propellant rocket engines
• CPC Class Codes: F02K 9/18 of the internal-burning type having a star or like shaped internal cavity
• CPC Class Codes: F02K 9/26 Burning control F02K9/10, F02K9/34, F02K9/86, F02K9/92 and F02K9/94 take precedence
• CPC Class Codes: F02K 9/346 Liners, e.g. inhibitors
• CPC Class Codes: F05D 2250/141 circular
• CPC Class Codes: F05D 2250/70 Shape
• CPC Class Codes: F05D 2260/96 Preventing, counteracting or reducing vibration or noise
• CPC Class Codes: F05D 2270/14 to control thermoacoustic behaviour in the combustion chambers counteracting noise or vibration F05D2260/96

Abstract

A launch vehicle comprising a casing, a solid propellant, a channel, a geometric feature, and a suppression structure. The solid propellant is located within the casing. The channel is through the solid propellant, and the geometric feature is in the channel. The suppression structure is located around a centerline for the channel and located upstream in a flow path from the geometric feature.

Claims

1. A launch vehicle comprising:

a casing;

a solid propellant located within the casing;

a channel through the solid propellant;

a geometric feature in the channel; and

a suppression structure, comprising a rod, located around a centerline for the channel and located entirely forward of the geometric feature with respect to a direction of travel of the launch vehicle, wherein the suppression structure is configured to reduce or eliminate an interaction of perturbations with the geometric feature in a manner that reduces or eliminates oscillations in thrust.

2. The launch vehicle of claim 1, wherein the suppression structure is configured to change a flow of exhaust around the geometric feature in the channel during burning of the solid propellant.

3. The launch vehicle of claim 1, wherein the suppression structure is configured to reduce feedback from vortical structures interacting with the geometric feature within the channel.

4. The launch vehicle of claim 1, wherein the suppression structure is secured to the casing.

5. The launch vehicle of claim 1, wherein the suppression structure is embedded within the solid propellant.

6. The launch vehicle of claim 1, wherein the rod is a circle-shaped rod having a cross-sectional diameter configured to generate perturbations at a frequency during a generation of thrust.

7. The launch vehicle of claim 1, wherein the rod is a circle-shaped rod having a diameter configured to generate perturbations at a radial location in a flow path during a generation of thrust.

8. The launch vehicle of claim 1, wherein the suppression structure has a distance from the geometric feature selected to reduce a generation of perturbations by the geometric feature in the channel.

9. The launch vehicle of claim 1, wherein the rod has a shape selected from one of a circle, a semi-circle, a star, a hexagon, and an octagon.

10. The launch vehicle of claim 1, wherein the rod comprises a first rod having a first shape nested inside of a second rod having a second shape.

11. The launch vehicle of claim 1, wherein the solid propellant comprises:

a first segment of solid propellant; and

a second segment of solid propellant located within the casing and adjacent to the first segment of solid propellant, wherein a gap is present between the first

segment of solid propellant and the second segment of solid propellant, and wherein the gap is the geometric feature.

12. The launch vehicle of claim 1, wherein the geometric feature is selected from one of a factory joint, a field joint, a first shape resulting from a first change in a cross-sectional diameter of a rod from which the suppression structure is constructed, a change in a diameter of the suppression structure, and a second shape resulting from a second change in a distance defined by a width of the channel relative to the centerline for the channel around which the suppression structure is located and from which perturbations are generated.

13. The launch vehicle of claim 1, wherein the geometric feature is selected from one of a gap and a step in a surface of the solid propellant in the channel.