US 12,031,507 B2
Augmented aerospike nozzle, engine including the augmented aerospike nozzle, and vehicle including the engine
Andrew Lapsa, Seattle, WA (US); and Thomas Feldman, Kent, WA (US)
Appl. No. 17/754,787
Filed by STOKE Space Technologies, Inc., Kent, WA (US)
PCT Filed Aug. 27, 2020, PCT No. PCT/US2020/048178
§ 371(c)(1), (2) Date Apr. 12, 2022,
PCT Pub. No. WO2021/108001, PCT Pub. Date Jun. 3, 2021.
Claims priority of provisional application 62/941,386, filed on Nov. 27, 2019.
Prior Publication US 2024/0083597 A1, Mar. 14, 2024
Int. Cl. F02K 9/97 (2006.01); B64G 1/00 (2006.01); F02K 9/64 (2006.01)
CPC F02K 9/97 (2013.01) [B64G 1/006 (2023.08); F02K 9/64 (2013.01); F02K 9/972 (2013.01); F05D 2240/1281 (2013.01)] 22 Claims
OG exemplary drawing
 
1. A multi-stage rocket, comprising:
a lower stage rocket;
an upper stage rocket separable from the lower stage rocket, the upper stage rocket including:
a forward end;
an aft end opposite the forward end;
a base at the aft end;
a sidewall extending forward from the base;
an engine configured for in-space propulsion and atmospheric landing propulsion, the engine at the aft end and including a high pressure chamber and an augmented aerospike nozzle that exhausts gas generated by the high pressure chamber, the augmented aerospike nozzle including:
an initial nozzle portion having a converging section, a diverging section downstream of the converging section, and a throat that defines a transition between the converging section and the diverging section;
a secondary nozzle portion downstream of the initial nozzle portion, the secondary nozzle portion including:
a centerbody extending aft of the initial nozzle portion;
an inner expansion surface defined by the centerbody;
an outer expansion surface outboard of the inner expansion surface and extending downstream from the diverging section of the initial nozzle portion; and
an expansion cavity defined between the inner expansion surface and the outer expansion surface;
an inflection point defined where the diverging section of the initial nozzle portion meets the outer expansion surface of the secondary nozzle portion; and
a nozzle exit defined at an aft end of the inner expansion surface and an aft end of the outer expansion surface;
wherein the base of the upper stage rocket includes an inner base surface and an outer base surface;
wherein the inner base surface is defined by a base of the centerbody;
wherein the outer base surface extends between the nozzle exit and the sidewall; and
wherein the inner base surface and the outer base surface form a continuously curved segment of an outer mold line of the upper stage rocket.