US 12,473,876 B2
Evanescent or fugacious thrust deflector
Jerome K. Fuller, Van Nuys, CA (US); Denise Galindo Burrell, Culver City, CA (US); Edward V. Wagner, Long Beach, CA (US); Andrew C. Cortopassi, Lakewood, CA (US); Jeffrey Arthur Lang, Torrance, CA (US); and Robert B. Pan, Torrance, CA (US)
Assigned to THE AEROSPACE CORPORATION, El Segundo, CA (US)
Filed by The Aerospace Corporation, El Segundo, CA (US)
Filed on Nov. 7, 2022, as Appl. No. 18/053,294.
Prior Publication US 2024/0151194 A1, May 9, 2024
Int. Cl. F02K 9/97 (2006.01); F02K 9/90 (2006.01)
CPC F02K 9/974 (2013.01) [F02K 9/90 (2013.01)] 6 Claims
OG exemplary drawing
 
4. An apparatus, comprising:
a nozzle configured to control a flow of thrust from the apparatus; and
an ablative material inside of or attached to the nozzle, the ablative material configured to initially deflect the thrust at a predefined angle through a plurality of curved vanes, wherein
the ablative material being configured to ablate-away, leaving un-deflected thrust for a majority of the burn,
wherein the ablative material comprises a hole in the center and the hole is positioned axially to an un-deflected thrust direction of the nozzle,
the ablative material together with the hole are configured to act as a timing feature, increasing a flow of thrust through the hole as the hole ablates away.