IP Library › Granted Patent US 12,601,314

Granted Patent B2

US 12,601,314 · App. 18/806,257 · Granted Apr 14, 2026

Reusable upper stage rocket

Inventors: Andrew Lapsa (Seattle, WA); Thomas Feldman (Kent, WA)

F02K9/97 B64G1/006 F05D2240/1281

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Quick Facts

Patent No.: US 12,601,314
App. No.: 18/806,257
Granted: Apr 14, 2026
Kind: B2

External Links

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Abstract

A reusable upper stage rocket or other atmospheric re-entry vehicle includes a nose, a base opposite the nose, and a propulsion engine toward the base. The propulsion engine includes a high pressure chamber and a nozzle configured to exhaust gas generated by the high pressure chamber. The nozzle includes an initial nozzle portion, a secondary nozzle portion downstream of the initial nozzle portion, and a nozzle exit at a downstream end of the secondary nozzle portion. The secondary nozzle portion includes an inner expansion surface, an outer expansion surface outboard of the inner expansion surface, and an expansion cavity defined between the inner expansion surface and the outer expansion surface.

Claims (133)

1 . A multi-stage rocket, comprising:

a lower stage rocket; and

an upper stage rocket separable from the lower stage rocket, the upper stage rocket including:

a nose;

a base opposite the nose; and

a propulsion engine toward the base, the propulsion engine including:

a high pressure chamber; and

an aerospike nozzle configured to exhaust gas generated by the high pressure chamber, the aerospike nozzle including:

a converging-diverging nozzle portion;

a secondary nozzle portion downstream of the converging-diverging nozzle portion, the secondary nozzle portion including an inner expansion surface, an outer expansion surface outboard of the inner expansion surface, and an expansion cavity defined between the inner expansion surface and the outer expansion surface; and

a nozzle exit at a downstream end of the secondary nozzle portion.

2 . The multi-stage rocket of claim 1 , wherein the aerospike nozzle further includes an inflection point defined where the converging-diverging nozzle portion meets the outer expansion surface of the secondary nozzle portion.

3 . The multi-stage rocket of claim 2 , wherein the converging-diverging nozzle portion includes 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;

wherein the diverging section of the converging-diverging nozzle portion includes an inner diverging surface and an outer diverging surface;

wherein the inner expansion surface of the secondary nozzle portion extends downstream of the inner diverging surface of the converging-diverging nozzle portion; and

wherein an inflection point is defined where the outer diverging surface of the converging-diverging nozzle portion meets the outer expansion surface of the secondary nozzle portion.

4 . The multi-stage rocket of claim 1 , wherein the base includes a first base portion inboard of the nozzle exit and a second base portion outboard of the nozzle exit;

wherein the secondary nozzle portion includes a centerbody; and

wherein the centerbody includes a centerbody sidewall that defines the inner expansion surface and a centerbody base that defines the first base portion.

5 . The multi-stage rocket of claim 4 , wherein the converging-diverging nozzle portion includes 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;

wherein the diverging section of the converging-diverging nozzle portion includes an inner diverging surface and an outer diverging surface;

wherein the inner expansion surface of the secondary nozzle portion extends downstream of the inner diverging surface of the converging-diverging nozzle portion; and

wherein an inflection point is defined where the outer diverging surface of the converging-diverging nozzle portion meets the outer expansion surface of the secondary nozzle portion.

6 . The multi-stage rocket of claim 4 , wherein the centerbody is a truncated toroidal aerospike.

7 . The multi-stage rocket of claim 4 , wherein the expansion cavity of the secondary nozzle portion extends annularly about the centerbody, and is concentrically aligned with the centerbody about a centerline of the upper stage rocket.

8 . The multi-stage rocket of claim 4 , wherein, in a cross-sectional plane parallel to a centerline of the upper stage rocket, a width of the centerbody continuously decreases in a downstream direction.

9 . The multi-stage rocket of claim 4 , wherein the upper stage rocket further includes a seal that allows the centerbody to gimbal relative to the outer expansion surface.

10 . The multi-stage rocket of claim 1 , wherein, in a cross-sectional plane parallel to a centerline of the upper stage rocket, a width of the expansion cavity continuously increases in a downstream direction.

11 . The multi-stage rocket of claim 1 , wherein, in a cross-sectional plane parallel to a centerline of the upper stage rocket, the outer expansion surface has a curved contour.

12 . The multi-stage rocket of claim 1 , wherein a contour of the outer expansion surface is curved such that, during in-space operation of the propulsion engine, the outer expansion surface captures a flow of the gas generated by the propulsion engine and turns the flow in a direction parallel to a centerline of the upper stage rocket to generate thrust.

13 . The multi-stage rocket of claim 1 , wherein the base includes a first base portion inboard of the nozzle exit and a second base portion outboard of the nozzle exit;

wherein the upper stage rocket further includes a sidewall extending from the base toward the nose; and

wherein the second base portion extends between the nozzle exit and the sidewall.

14 . The multi-stage rocket of claim 13 , wherein the outer expansion surface of the secondary nozzle portion remains positionally fixed relative to the sidewall.

15 . The multi-stage rocket of claim 1 , wherein the base includes a first base portion inboard of the nozzle exit and a second base portion outboard of the nozzle exit;

wherein the base has a dome shape defined by the first base portion and the second base portion.

16 . The multi-stage rocket of claim 1 , wherein the propulsion engine is configured to provide propulsive thrust during nose-first travel of the upper stage rocket and retro-propulsive thrust during base-first travel of the upper stage rocket.

17 . The multi-stage rocket of claim 1 , wherein the propulsion engine is configured such that, during atmospheric landing of the upper stage rocket, a jet of high pressure gas exits the high pressure chamber and expands along the inner expansion surface of the secondary nozzle portion, and the jet does not interact with the outer expansion surface of the secondary nozzle portion.

18 . The multi-stage rocket of claim 1 , wherein the propulsion engine is configured such that, during in-space operation of the upper stage rocket, a jet of high pressure gas exits the high pressure chamber and expands along the inner expansion surface and the outer expansion surface of the secondary nozzle portion to produce thrust in a direction parallel to a centerline of the upper stage rocket.

19 . The multi-stage rocket of claim 1 , wherein the propulsion engine is configured such that, during atmospheric landing of the upper stage rocket, a jet of high pressure gas exits the high pressure chamber and expands along the inner expansion surface of the secondary nozzle portion, and the jet does not interact with the outer expansion surface of the secondary nozzle portion; and

wherein the propulsion engine is configured such that, during in-space operation of the upper stage rocket, a jet of high pressure gas exits the high pressure chamber and expands along the inner expansion surface and the outer expansion surface of the secondary nozzle portion to produce thrust in a direction parallel to a centerline of the upper stage rocket.

20 . The multi-stage rocket of claim 1 , wherein the aerospike nozzle is an annular aerospike nozzle.

21 . The multi-stage rocket of claim 1 , wherein the aerospike nozzle is a linear aerospike nozzle.

22 . An atmospheric re-entry vehicle, comprising:

a nose;

a base opposite the nose; and

a propulsion engine toward the base, the propulsion engine including:

a high pressure chamber; and

an aerospike nozzle configured to exhaust gas generated by the high pressure chamber, the aerospike nozzle including:

a converging-diverging nozzle portion;

a nozzle exit at a downstream end of the secondary nozzle portion.

23 . The atmospheric re-entry vehicle of claim 22 , wherein the aerospike nozzle further includes an inflection point defined where the converging-diverging nozzle portion meets the outer expansion surface of the secondary nozzle portion.

24 . The atmospheric re-entry vehicle of claim 22 , wherein the converging-diverging nozzle portion includes 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;

wherein the diverging section of the converging-diverging nozzle portion includes an inner diverging surface and an outer diverging surface;

wherein the inner expansion surface of the secondary nozzle portion extends downstream of the inner diverging surface of the converging-diverging nozzle portion; and

wherein an inflection point is defined where the outer diverging surface of the converging-diverging nozzle portion meets the outer expansion surface of the secondary nozzle portion.

25 . The atmospheric re-entry vehicle of claim 22 , wherein the base includes a first base portion inboard of the nozzle exit and a second base portion outboard of the nozzle exit;

wherein the secondary nozzle portion includes a centerbody; and

wherein the centerbody includes a centerbody sidewall that defines the inner expansion surface and a centerbody base that defines the first base portion.

26 . The atmospheric re-entry vehicle of claim 25 , wherein the converging-diverging nozzle portion includes 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;

wherein the diverging section of the converging-diverging nozzle portion includes an inner diverging surface and an outer diverging surface;

wherein the inner expansion surface of the secondary nozzle portion extends downstream of the inner diverging surface of the converging-diverging nozzle portion; and

wherein an inflection point is defined where the outer diverging surface of the converging-diverging nozzle portion meets the outer expansion surface of the secondary nozzle portion.

27 . The atmospheric re-entry vehicle of claim 25 , wherein the centerbody is a truncated toroidal aerospike.

28 . The atmospheric re-entry vehicle of claim 25 , wherein the expansion cavity of the secondary nozzle portion extends annularly about the centerbody, and is concentrically aligned with the centerbody about a centerline of the vehicle.

29 . The atmospheric re-entry vehicle of claim 25 , wherein, in a cross-sectional plane parallel to a centerline of the vehicle, a width of the centerbody continuously decreases in a downstream direction.

30 . The atmospheric re-entry vehicle of claim 25 , wherein the vehicle further includes a seal that allows the centerbody to gimbal relative to the outer expansion surface.

31 . The atmospheric re-entry vehicle of claim 22 , wherein, in a cross-sectional plane parallel to a centerline of the vehicle, a width of the expansion cavity continuously increases in a downstream direction.

32 . The atmospheric re-entry vehicle of claim 22 , wherein, in a cross-sectional plane parallel to a centerline of the vehicle, the outer expansion surface has a curved contour.

33 . The atmospheric re-entry vehicle of claim 22 , wherein a contour of the outer expansion surface is curved such that, during in-space operation of the propulsion engine, the outer expansion surface captures a flow of the gas generated by the propulsion engine and turns the flow in a direction parallel to a centerline of the vehicle to generate thrust.

34 . The atmospheric re-entry vehicle of claim 22 , wherein the base includes a first base portion inboard of the nozzle exit and a second base portion outboard of the nozzle exit;

wherein the vehicle further includes a sidewall extending from the base toward the nose; and

wherein the second base portion extends between the nozzle exit and the sidewall.

35 . The atmospheric re-entry vehicle of claim 34 , wherein the outer expansion surface of the secondary nozzle portion remains positionally fixed relative to the sidewall.

36 . The atmospheric re-entry vehicle of claim 22 , wherein the base includes a first base portion inboard of the nozzle exit and a second base portion outboard of the nozzle exit; and

wherein the base has a dome shape defined by the first base portion and the second base portion.

37 . The atmospheric re-entry vehicle of claim 22 , wherein the propulsion engine is configured to provide propulsive thrust during nose-first travel of the vehicle and retro-propulsive thrust during base-first travel of the vehicle.

38 . The atmospheric re-entry vehicle of claim 22 , wherein the propulsion engine is configured such that, during atmospheric landing of the vehicle, a jet of high pressure gas exits the high pressure chamber and expands along the inner expansion surface of the secondary nozzle portion, and the jet does not interact with the outer expansion surface of the secondary nozzle portion.

39 . The atmospheric re-entry vehicle of claim 22 , wherein the propulsion engine is configured such that, during in-space operation of the vehicle, a jet of high pressure gas exits the high pressure chamber and expands along the inner expansion surface and the outer expansion surface of the secondary nozzle portion to produce thrust in a direction parallel to a centerline of the vehicle.

40 . The atmospheric re-entry vehicle of claim 22 , wherein the propulsion engine is configured such that, during atmospheric landing of the vehicle, a jet of high pressure gas exits the high pressure chamber and expands along the inner expansion surface of the secondary nozzle portion, and the jet does not interact with the outer expansion surface of the secondary nozzle portion; and

wherein the propulsion engine is configured such that, during in-space operation of the vehicle, a jet of high pressure gas exits the high pressure chamber and expands along the inner expansion surface and the outer expansion surface of the secondary nozzle portion to produce thrust in a direction parallel to a centerline of the vehicle.

41 . The atmospheric re-entry vehicle of claim 22 , wherein the aerospike nozzle is an annular aerospike nozzle.

42 . The atmospheric re-entry vehicle of claim 22 , wherein the aerospike nozzle is a linear aerospike nozzle.

43 . The atmospheric re-entry vehicle of claim 22 , wherein the atmospheric re-entry vehicle is an upper stage rocket.

44 . The atmospheric re-entry vehicle of claim 22 , wherein the atmospheric re-entry vehicle is a spacecraft.

45 . An atmospheric re-entry vehicle, comprising:

a nose;

a base opposite the nose; and

a propulsion engine toward the base, the propulsion engine including:

a high pressure chamber; and

a nozzle configured to exhaust gas generated by the high pressure chamber, the nozzle including:

an initial nozzle portion;

a secondary nozzle portion downstream of the initial nozzle portion, the secondary nozzle portion including an inner expansion surface, an outer expansion surface outboard of the inner expansion surface, and an expansion cavity defined between the inner expansion surface and the outer expansion surface; and

a nozzle exit at a downstream end of the secondary nozzle portion.

46 . The atmospheric re-entry vehicle of claim 45 , wherein the nozzle further includes an inflection point defined where the initial nozzle portion meets the outer expansion surface of the secondary nozzle portion.

47 . The atmospheric re-entry vehicle of claim 45 , wherein the initial nozzle portion includes 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;

wherein the diverging section of the initial nozzle portion includes an inner diverging surface and an outer diverging surface;

wherein the inner expansion surface of the secondary nozzle portion extends downstream of the inner diverging surface of the initial nozzle portion; and

wherein an inflection point is defined where the outer diverging surface of the initial nozzle portion meets the outer expansion surface of the secondary nozzle portion.

48 . The atmospheric re-entry vehicle of claim 45 , wherein the base includes a first base portion inboard of the nozzle exit and a second base portion outboard of the nozzle exit;

wherein the secondary nozzle portion includes a centerbody; and

wherein the centerbody includes a centerbody sidewall that defines the inner expansion surface and a centerbody base that defines the first base portion.

49 . The atmospheric re-entry vehicle of claim 48 , wherein the initial nozzle portion includes 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;

wherein the diverging section of the initial nozzle portion includes an inner diverging surface and an outer diverging surface;

wherein the inner expansion surface of the secondary nozzle portion extends downstream of the inner diverging surface of the initial nozzle portion; and

wherein an inflection point is defined where the outer diverging surface of the initial nozzle portion meets the outer expansion surface of the secondary nozzle portion.

50 . The atmospheric re-entry vehicle of claim 48 , wherein the centerbody is a truncated toroidal aerospike.

51 . The atmospheric re-entry vehicle of claim 48 , wherein the expansion cavity of the secondary nozzle portion extends annularly about the centerbody, and is concentrically aligned with the centerbody about a centerline of the vehicle.

52 . The atmospheric re-entry vehicle of claim 48 , wherein, in a cross-sectional plane parallel to a centerline of the vehicle, a width of the centerbody continuously decreases in a downstream direction.

53 . The atmospheric re-entry vehicle of claim 48 , wherein the vehicle further includes a seal that allows the centerbody to gimbal relative to the outer expansion surface.

54 . The atmospheric re-entry vehicle of claim 45 , wherein, in a cross-sectional plane parallel to a centerline of the vehicle, a width of the expansion cavity continuously increases in a downstream direction.

55 . The atmospheric re-entry vehicle of claim 45 , wherein, in a cross-sectional plane parallel to a centerline of the vehicle, the outer expansion surface has a curved contour.

56 . The atmospheric re-entry vehicle of claim 45 , wherein a contour of the outer expansion surface is curved such that, during in-space operation of the propulsion engine, the outer expansion surface captures a flow of the gas generated by the propulsion engine and turns the flow in a direction parallel to a centerline of the vehicle to generate thrust.

57 . The atmospheric re-entry vehicle of claim 45 , wherein the base includes a first base portion inboard of the nozzle exit and a second base portion outboard of the nozzle exit;

wherein the vehicle further includes a sidewall extending from the base toward the nose; and

wherein the second base portion extends between the nozzle exit and the sidewall.

58 . The atmospheric re-entry vehicle of claim 57 , wherein the outer expansion surface of the secondary nozzle portion remains positionally fixed relative to the sidewall.

59 . The atmospheric re-entry vehicle of claim 45 , wherein the base includes a first base portion inboard of the nozzle exit and a second base portion outboard of the nozzle exit; and

wherein the base has a dome shape defined by the first base portion and the second base portion.

60 . The atmospheric re-entry vehicle of claim 45 , wherein the propulsion engine is configured to provide propulsive thrust during nose-first travel of the vehicle and retro-propulsive thrust during base-first travel of the vehicle.

61 . The atmospheric re-entry vehicle of claim 45 , wherein the propulsion engine is configured such that, during atmospheric landing of the vehicle, a jet of high pressure gas exits the high pressure chamber and expands along the inner expansion surface of the secondary nozzle portion, and the jet does not interact with the outer expansion surface of the secondary nozzle portion.

62 . The atmospheric re-entry vehicle of claim 45 , wherein the propulsion engine is configured such that, during in-space operation of the vehicle, a jet of high pressure gas exits the high pressure chamber and expands along the inner expansion surface and the outer expansion surface of the secondary nozzle portion to produce thrust in a direction parallel to a centerline of the vehicle.

63 . The atmospheric re-entry vehicle of claim 45 , wherein the propulsion engine is configured such that, during atmospheric landing of the vehicle, a jet of high pressure gas exits the high pressure chamber and expands along the inner expansion surface of the secondary nozzle portion, and the jet does not interact with the outer expansion surface of the secondary nozzle portion; and

64 . The atmospheric re-entry vehicle of claim 45 , wherein the nozzle is an annular aerospike nozzle.

65 . The atmospheric re-entry vehicle of claim 45 , wherein the nozzle is a linear aerospike nozzle.

66 . The atmospheric re-entry vehicle of claim 45 , wherein the atmospheric re-entry vehicle is an upper stage rocket.

67 . The atmospheric re-entry vehicle of claim 45 , wherein the atmospheric re-entry vehicle is a spacecraft.

68 . The atmospheric re-entry vehicle of claim 45 , wherein the propulsion engine is a plug cluster engine.

69 . The atmospheric re-entry vehicle of claim 68 , wherein the high pressure chamber is a first high pressure chamber of a plurality of high pressure chambers that are spaced relative to one another;

wherein the initial nozzle portion is a first initial nozzle portion of a plurality of initial nozzle portions that are spaced relative to one another; and

wherein each initial nozzle portion of the plurality of initial nozzle portions is disposed relative to corresponding high pressure chamber of the plurality of high pressure chambers.

Assignments (1)

SECURITY INTEREST Recorded Jun 16, 2025

From: STOKE SPACE TECHNOLOGIES, INC.; STOKE SPACE FEDERAL, INC.

To: FIRST-CITIZENS BANK & TRUST COMPANY, AS AGENT

Reel/Frame 071425/0813 →

Continuity (4)

Continuation 17407472 · Aug 20, 2021

Continuation PCTUS2020048178 · Aug 27, 2020

Provisional Application 62941386 · Nov 27, 2019

Related Publication 20240401548A1 · Dec 5, 2024

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“Pegasus VTOVL,” Web page <http://www.astronautix.com/p/pegasusvtovl.html>, 4 pages [retrieved on Mar. 20, 2023]. [cited by applicant]

“Project Selena,” Web page <http://www.astronautix.com/p/projectselena.html>, 3 pages [retrieved on Mar. 20, 2023]. [cited by applicant]

“Rombus,” Web page <http://www.astronautix.com/r/rombus.html>, 4 pages [retrieved on Mar. 20, 2023]. [cited by applicant]

“SASSTO,” Web page <http://www.astronautix.com/s/sassto.html>, 5 pages [retrieved on Mar. 20, 2023]. [cited by applicant]

“Philip Bono Personal Papers,” Web page <https://sandiegoairandspace.org/collection/item/philip-bono-personal-papers>, 5 pages [retrieved on Mar. 21, 2023]. [cited by applicant]

Bono, et al.; Frontiers of Space: The Pocket Encyclopedia of Spaceflight in Color (London, Blandford Press, 1969), pp. 64-66, 68-72, 78, 147-163, 171, 180, 206-207, 246-247. ISBN 0-7137-3504-X. [cited by applicant]

Select photos from Flickr album entitled “Philip Bono Collection Image,” uploaded Jun. 20, 2016 by user “SDASM Archives” [retrieved on Mar. 21, 2023]. Retrieved from Internet: <https://www.flickr.com/photos/sdasmarchive… [cited by applicant]

Automated transcript from YouTube video entitled “How Stoke Space's Unique Rocket Works // Exclusive Tour & Interview,” 21 pages, uploaded on Feb. 4, 2023 by user “Everyday Astronaut”. Retrieved from Internet: <https://… [cited by applicant]

Automated transcript from YouTube video entitled “We are Stoke Space”, 2 pages, uploaded on Dec. 17, 2022 by user “Stoke Space”. Retreived from Internet: <https://www.youtube.com/watch?v=VzqhZLgpiv0&t=46s>. [cited by applicant]

Angelino, Gianfranco; “Approximate Method for Plug Nozzle Design” ; AIAA Journal, vol. 2, Issue 10; Oct. 1964; 2 Pages. [cited by applicant]

Dnofri, Marcello, et al; “Plug Nozzles: Summary of Flow Features and Engine Performance” ; 40th AIAA Aerospace Sciences Meeting & Exhibit; Reno, NV; Jan. 14, 2002; 27 Pages. [cited by applicant]

International Search Report and Written Opinion of the International Searching Authority; Application No. PCT/US 20/48178; Completed: Apr. 26, 2021; Mailing Date: May 5, 2021; 8 Pages. [cited by applicant]

Hudson, G. C., “Phoenix—A commercial, reusable single-stage launch vehicle”, Pacific American Launch Systems, Phoenix Reference, 1985. [cited by applicant]

Hudson, Gary. (1992). History of the Phoenix VTOL SSTO and recent developments in single-stage launch systems. [cited by applicant]

Undated 1 page engineering document received electronically from third party on Aug. 11, 2025. Document was received as a PDF with the name “PHOENIX2_LINEUP_1988-12 copy.pdf”. Applicant does not admit that the document … [cited by applicant]