Patent US3635404A successfully refreshed from Google Patents.
US3635404A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Spin stabilizing rocket nozzle
Assignee: United States Department of the Navy
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Filing: 1970-06-18
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Granted: 1972-01-18
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Expires: 1990-06-18
Abstract
Abstract A rocket nozzle having a plurality of internal vanes located downstream of the nozzle throat for imparting rotational spin to the rocket about its longitudinal axis. Each vane may have a nonablative body having a cross section symmetric with the nozzle axis and a consummable ablative body attached thereto to provide a composite cross section asymmetric to the nozzle axis. The ablative material, imparts spin stabilization to the rocket leaving only the symmetric nonablative vane portions, thus preventing excessive spin rates.
Inventors
- 👤 Wayne J Hopkins
- 👤 James K Watson
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-25 18:03
CPC Classifications
F; F42; F42B; F42B10/00; F42B10/02; F42B10/26; F42B10/28; F42B10/30; F02; F02K; F02K9/00; F02K9/97; F02K9/974; Y; Y10; Y10S; Y10S239/00; Y10S239/19
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
85 words
A reaction thrust nozzle for spin stabilizing a rocket comprising: a convergent-divergent thrust nozzle adapted to be mounted in operative alignment with a rocket motor, a plurality of elongate spin inducing vanes mounted in said nozzle, said vanes each increasing in transverse cross section from its forward end toward its rearward end and having a first longitudinal sidewall thereof positioned parallel to the longitudinal axis of said nozzle and having a second longitudinal sidewall thereof angularly displaced relative to the longitudinal axis of said nozzle.
Claim 2
Dependent Claim
85 words
A reaction thrust nozzle for spin stabilizing a rocket comprising: a convergent-divergent thrust nozzle adapted to be mounted in operative alignment with a rocket motor, a plurality of elongate spin inducing vanes mounted in said nozzle, said vanes each increasing in transverse cross section from its forward end toward its rearward end and having a first longitudinal sidewall thereof positioned parallel to the longitudinal axis of said nozzle and having a second longitudinal sidewall thereof angularly displaced relative to the longitudinal axis of said nozzle.
Claim 3
Dependent Claim
18 words
A device of claim 1 wherein at least a portion of each vane is formed of ablative material.
Claim 4
Dependent Claim
32 words
The device of claim 1 wherein said vanes are mounted in said nozzle at locations downstream of the nozzle throat and being equiangularly spaced radially about the longitudinal axis of said nozzle.
Claim 5
Dependent Claim
65 words
The device of claim 3 wherein each of said vanes includes a first body portion formed of nonablative material and having a cross section symmetric with the longitudinal axis of said rocket, and a second body portion formed of ablative material having a cross section asymmetric with the longitudinal axis of the nozzle, said second body portion being fixedly mounted to the first body portion.
Claim 6
Dependent Claim
82 words
The device of claim 4 wherein said first body portion is formed of flat plates having parallel opposed sidewalls, said plate sidewalls being tapered on their upstream ends to form a knife edge, said second body portion having the configuration of a solid right triangle and being mountEd upon said first body portion such that the side of said second body portion defined by the hypotenuse of the right triangle forms a continuation of the tapered edge of said first body portion.
Claim 7
Dependent Claim
21 words
The device of claim 1 wherein at least a portion of each of said vanes is formed of a disintegrating material.
Claim 8
Dependent Claim
37 words
The device of claim 1 wherein each of said vanes being laterally separated from adjacent vanes by a distance preventing interference with the shock waves fronts occurring at said adjacent vanes when subjected to supersonic gas flow.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1975-01-17 | 1975-07-19 | 1976-01-18 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-01-17 | 1979-07-19 | 1980-01-18 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-01-17 | 1983-07-19 | 1984-01-18 | $7700.00 | Window Closed / Lapsed |