US 12,378,009 B2
Heat fins for heat dissipation of rocket components
David Harper, Huntsville, AL (US); Jeramy Kimball, Seattle, WA (US); Logan Sailer, Seattle, WA (US); and Curtis Wen, Seattle, WA (US)
Assigned to Blue Origin Manufacturing, LLC, Huntsville, AL (US)
Filed by Blue Origin Manufacturing, LLC, Huntsville, AL (US)
Filed on May 21, 2024, as Appl. No. 18/669,991.
Application 18/669,991 is a division of application No. 17/466,510, filed on Sep. 3, 2021, granted, now 12,024,318.
Prior Publication US 2024/0300676 A1, Sep. 12, 2024
Int. Cl. B64G 1/58 (2006.01); B64G 1/40 (2006.01); F28F 3/02 (2006.01)
CPC B64G 1/58 (2013.01) [B64G 1/4021 (2023.08); F28F 3/02 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A method of making a component of a rocket, the method comprising:
forming a shell having a cavity that is created by adjoining multiple panels to one another, wherein the multiple panels comprise:
a first panel that includes first heat fins having a first thermal capacity to component stiffness (TCCS) ratio, the first panel being located at a first position of the shell and having a first thermal profile, and
a second panel that includes second heat fins having a second TCCS ratio different from the first TCCS ratio, the second panel located at a second position of the shell and having a second thermal profile that differs from the first thermal profile; and
adjoining a strake to the shell such that the second panel at the second position is in contact with the strake or closer to the strake than the first panel at the first position.