LAUNCH VEHICLE WITH RING BAFFLES

1 . A propellant tank to be used with a launch vehicle, the propellant tank comprising: at least one ring baffle comprising a plurality of corrugated surfaces which are aligned circumferentially with respect to a longitudinal axis of the propellant tank, wherein folds of the plurality of corrugated surfaces rise and fall in a first direction which is along the longitudinal axis, wherein the at least one ring baffle is to be on an interior circumference of the propellant tank, and wherein the corrugated surfaces extend in a second direction which is along a lateral axis, relative to the longitudinal axis, and which is of a predetermined width from the interior circumference of the propellant tank.

2 . The propellant tank of claim 1 , wherein the propellant tank is subject to propellant loads in a vertically aligned or substantially vertically aligned position with respect to a surface of a launch pad.

3 . The propellant tank of claim 1 , wherein the corrugated surfaces are comprised in individual corrugated sections having attachment points which are at a first end and a second end which are along a tangential direction relative to the interior circumference of the propellant tank.

4 . The propellant tank of claim 1 , wherein the corrugated surfaces are comprised in individual corrugated sections which are associated together by a spine section which comprises a strut section.

5 . The propellant tank of claim 1 , wherein the corrugated surfaces are comprised in individual corrugated sections which are associated together by a spine section which comprises a drainage area to support drainage along the lateral axis.

6 . The propellant tank of claim 1 , wherein the corrugated surfaces are comprised in individual corrugated sections and wherein the individual corrugated sections comprise an incline which is along a tangential direction relative to the interior circumference of the propellant tank, the incline to support drainage of the propellant to a drainage area which is between adjacent ones of the individual corrugated sections.

7 . The propellant tank of claim 1 , wherein the corrugated surfaces are comprised in individual corrugated sections, and wherein individual ones of the corrugated sections comprise a strut section, the strut section to be rotatable about the longitudinal axis and to be removably associated with the interior circumference of the propellant tank.

8 . The propellant tank of claim 1 , wherein the corrugated surfaces are comprised in individual corrugated sections which are associated together by a spine section, the spine section to be removably associated with the interior circumference of the propellant tank.

9 . The propellant tank of claim 1 , wherein one or more of the corrugated surfaces or support sections for the corrugated surfaces comprise one or more of a metal material, a plastic material, or a composite material.

10 . The propellant tank of claim 1 , wherein the at least one ring baffle comprises a plurality of ring baffles with one or more spatial separations therebetween, the one or more spatial separations along the longitudinal axis of the propellant tank.

11 . A ring baffle to be used in a propellant tank, the ring baffle comprising a plurality of corrugated surfaces which are aligned circumferentially with respect to a longitudinal axis of the propellant tank, wherein folds of the plurality of corrugated surfaces rise and fall in a first direction which is along the longitudinal axis, wherein the ring baffle is to be on an interior circumference of the propellant tank, and wherein the corrugated surfaces extend in a second direction which is along a lateral axis, relative to the longitudinal axis, and which is of a predetermined width from the interior circumference of the propellant tank.

12 . The ring baffle of claim 11 , wherein the corrugated surfaces are comprised in individual corrugated sections having attachment points which are at a first end and a second end which are along a tangential direction relative to the interior circumference of the propellant tank, relative to the lateral axis.

13 . The ring baffle of claim 11 , wherein the corrugated surfaces are comprised in individual corrugated sections which are associated together by a spine section which comprises a drainage area to support drainage along the lateral axis.

14 . The ring baffle of claim 11 , wherein the corrugated surfaces are comprised in individual corrugated sections and wherein the individual corrugated sections comprise an incline which is along a tangential direction relative to the interior circumference of the propellant tank, the incline to support drainage of the propellant to a drainage area which is between adjacent ones of the individual corrugated sections.

15 . A method for a propellant tank, the method comprising:

preparing a plurality of ring baffles to be used in the propellant tank, individual ones of the ring baffles comprising a plurality of corrugated surfaces which are aligned circumferentially with respect to a longitudinal axis of the propellant tank, wherein folds of the plurality of corrugated surfaces rise and fall in a first direction which is along the longitudinal axis, and wherein the plurality of ring baffles are to be of a predetermined width with respect to an interior circumference of the propellant tank;

determining locations for the plurality of ring baffles on an interior circumference of the propellant tank; and

installing the ring baffles at the determined locations, with the corrugated surfaces extending in a second direction which is along a lateral axis, relative to the longitudinal axis.

16 . The method of claim 15 , further comprising:

determining a type of propellant to be used with the propellant tank; and

determining the locations of the plurality of ring baffles based in part on the type of propellant.

17 . The method of claim 15 , further comprising:

aligning individual corrugated sections circumferentially to provide one of the plurality of corrugated surfaces;

associating the individual corrugated sections to individual spine sections using attachment points which are at a first end and a second end of the individual corrugated sections, the first end and the second end being along a tangential direction relative to the interior circumference of the propellant tank;

associating the individual spine sections with individual strut sections; and

associating the individual spine sections and the individual strut sections to the interior circumference of the propellant tank.

18 . The method of claim 15 , further comprising:

associating the individual spine sections and the individual strut sections to the interior circumference of the propellant tank at a predetermined one of the locations based in part on a type of the propellant.

19 . The method of claim 15 , further comprising:

preparing the individual corrugated sections with a respective incline which is along a tangential direction relative to the interior circumference of the propellant tank, the incline to support drainage of the propellant to a drainage area which is between adjacent ones of the individual corrugated section; and

aligning individual corrugated sections circumferentially to provide one of the plurality of corrugated surfaces by aligning the respective incline towards an individual one of a plurality of spine sections to support drainage of propellant towards the plurality of spine sections.

20 . The method of claim 15 , further comprising:

associating the individual corrugated sections with individual spine sections using tabs of varying heights at one end of the individual corrugated sections, the tabs of varying heights to support a respective incline within the individual spine sections; and

aligning individual corrugated sections circumferentially to provide one of the plurality of corrugated surfaces by aligning the respective incline towards an individual one of a plurality of spine sections to support drainage which is along the lateral axis for the propellant.