US3784109A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Deployable nozzle extension for rocket engines
Assignee: Textron Inc
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Filing: 1972-05-22
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Granted: 1974-01-08
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Expires: 1992-05-22
Abstract
Abstract A deployable nozzle for rocket engines and method of making same is disclosed in which the extension initially is in collapsed state and is provided with a detachable cover so that internal pressure may be utilized to extend and deploy the extension. The extension includes an outer convolution of annular divergent frusto-conical form joined along a fold line to an intermediate convolution also of frusto-conical form but directed oppositely from the outer convolution and the intermediate convolution is joined at its small end to a divergent frusto-conical rocket nozzle portion through a relatively narrow cylindrical band which surrounds the divergent nozzle portion and is joined to it at a point spaced from the end of such nozzle portion. The length of this band is of predetermined relation with respect to the length of the free end portion of the nozzle extension such that when the nozzle extension is deployed, it will unroll over the edge of the free end of the nozzle extension to embrace it and form a non-offset and coplanar extension of the inner surface of the rocket nozzle portion.
Inventors
- 👤 J Dueringer
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-03 01:15
CPC Classifications
F; F02; F02K; F02K9/00; F02K9/97; F02K9/976
Claims Analysis
Total Claims: 16
Claim 1
Independent Claim
204 words
A rocket engine nozzle extension for use with a rocket engine having a combustion chamber discharging to a restricted throat followed by a divergent conical nozzle section terminating in a frusto-conical free end portion, said extension being deployable from an intially collapsed state to form an expansion ratioincreasing extension of said divergent conical section, said nozzle extension comprising: a cylindrical section secured exteriorally to said divergent conical section in coaxial surrounding relation thereto and extending forwardly therefrom toward said combustion chamber; a frusto-conical intermediate convolution extending divergently and forwardly from said cylindrical section; and a frusto-conical outer convolution extending divergently and rearwardly in surrounding relation to said intermediate convoltuion, said outer convolution being joined to said intermediate convolution along an annular fold; said cylindrical section being of a diameter sufficiently smaller than the diameter of the free end edge of said frustoconical free end portion and of a length relative to the length of said frusto-conical free end portion as to permit said annular fold to roll through said intermediate convolution and said cylindrical section thereby lengthening said outer convolution and causing it to form a substantially smooth extension of said nozzle section at said free end edge of said frusto-conical free end portion.
Claim 2
Dependent Claim
204 words
A rocket engine nozzle extension for use with a rocket engine having a combustion chamber discharging to a restricted throat followed by a divergent conical nozzle section terminating in a frusto-conical free end portion, said extension being deployable from an intially collapsed state to form an expansion ratioincreasing extension of said divergent conical section, said nozzle extension comprising: a cylindrical section secured exteriorally to said divergent conical section in coaxial surrounding relation thereto and extending forwardly therefrom toward said combustion chamber; a frusto-conical intermediate convolution extending divergently and forwardly from said cylindrical section; and a frusto-conical outer convolution extending divergently and rearwardly in surrounding relation to said intermediate convoltuion, said outer convolution being joined to said intermediate convolution along an annular fold; said cylindrical section being of a diameter sufficiently smaller than the diameter of the free end edge of said frustoconical free end portion and of a length relative to the length of said frusto-conical free end portion as to permit said annular fold to roll through said intermediate convolution and said cylindrical section thereby lengthening said outer convolution and causing it to form a substantially smooth extension of said nozzle section at said free end edge of said frusto-conical free end portion.
Claim 3
Dependent Claim
30 words
A rocket nozzle extension as defined in claim 1 including means for causing said annular fold to roll through said intermediatE convolution and said cylindrical section to deploy the extension.
Claim 4
Dependent Claim
25 words
A rocket nozzle extension as defined in claim 2 wherein said means comprises a cover detachably fixed to the open end of said outer convolution.
Claim 5
Dependent Claim
149 words
A deployable nozzle for rocket engines comprising, in combination: an inner section having a divergent inner surface of generally conical form; an intermediate convolution surrounding said inner section and having an outer surface diverging in the direction opposite to the divergence of said inner surface and adapted to be deployed into registry with said inner surface of the inner section with minimal radial offset with respect thereto; a cylindrical band joining the smaller end of said intermediate convolution to said inner section along a circumferential line located in spaced relation to the larger diameter free end edge of said inner section; an outer convolution surrounding said intermediate convolution and having a divergent inner surface facing the same direction as the inner surface of said inner section; and an annular fold section joining the larger diameter end of said intermediate convolution to the smaller diameter end of said outer convolution.
Claim 6
Dependent Claim
149 words
A deployable nozzle for rocket engines comprising, in combination: an inner section having a divergent inner surface of generally conical form; an intermediate convolution surrounding said inner section and having an outer surface diverging in the direction opposite to the divergence of said inner surface and adapted to be deployed into registry with said inner surface of the inner section with minimal radial offset with respect thereto; a cylindrical band joining the smaller end of said intermediate convolution to said inner section along a circumferential line located in spaced relation to the larger diameter free end edge of said inner section; an outer convolution surrounding said intermediate convolution and having a divergent inner surface facing the same direction as the inner surface of said inner section; and an annular fold section joining the larger diameter end of said intermediate convolution to the smaller diameter end of said outer convolution.
Claim 7
Dependent Claim
157 words
A deployable nozzle for rocket engines as defined in claim 4 wherein the free end of said inner section is bevelled to present an outer face substantially parallel to and concentric with the axis of said nozzle to intersect said inner surface of the inner section at said free end edge; and the diameter of said cylindrical band being sufficiently smaller than the diameter of said free end edge and of a length relative to the length of that portion of said inner section which is beyond said cylindrical band as to permit said annular fold section to roll through said intermediate convolution and said cylindrical band thereby lengthening said outer convolution and causing it to form an extension of said inner section beginning at said free end edge and with a rolled over portion of said cylindrical band overlying and in closely spaced relation to said outer face of the free end of said inner section.
Claim 8
Dependent Claim
45 words
A deployable nozzle for rocket engines as defined in claim 5 wherein said inner section comprises a first frusto-conical portion remote from said free end edge of the inner section and a second frusto-conical portion attached to and forming a continuation of said first portion.
Claim 9
Dependent Claim
46 words
A deployable nozzle for rocket engines as defined in claim 6 and in combination therewith: a rocket engine having a combination chamber and a restricted throat; said first frusto-conical portion being integrally joined to said rocket engine and presenting a divergent section from said restricted throat.
Claim 10
Dependent Claim
45 words
A deployable nozzle for rocket engines as defined in claim 5 and in combination therewith: a rocket engine having a combustion chamber and a restricted throat; said inner section being integrally joined to said rocket engine and presenting a divergent section from said restricted throat.
Claim 11
Dependent Claim
45 words
A deployable nozzle for rocket engines as defined in claim 4 and in combination therewith: a rocket engine having a combustion chamber and a restricted throat; said inner section being integrally joined to said rocket engine and presenting a divergent section from said restricted throat.
Claim 12
Dependent Claim
45 words
A deployable nozzle for rocket engines ad defined in claim 4 wherein said inner section comprises a first frusto-conical portion remote from said free end edge of the inner section and a second frusto-conical portion attached to and forming a continuation of said first portion.
Claim 13
Dependent Claim
45 words
A deployable nozzle for rocket engines as defined in claim 10 and in combination therewith: a rocket engine having a combustion chamber and a restricted throat; said frusto-conical portion being integrally joined to said rocket engine and presenting a divergent section from said restricted throat.
Claim 14
Dependent Claim
78 words
A rocket engine nozzle extension as defined in claim 1 wherein said frusto-coNical free end portion terminates in a bevel presenting an outer face substantially parallel to and concentric with the longitudinal axis of the nozzle extension and which outer face intersects the inner surface of said free end portion to define said free end edge, a rolled over portion of said cylindrical section overlying said outer face in closely spaced relation thereto when the extension is deployed.
Claim 15
Dependent Claim
46 words
A rocket engine nozzle extension as defined in claim 12 wherein said divergent conical nozzle portion of the rocket engine comprises a first frusto-conical section extending from said restricted throat and a second frusto-conical section forming a continuation of and attached to said first frusto-conical section.
Claim 16
Dependent Claim
46 words
A rocket engine nozzle extension as defined in claim 1 wherein said divergent conical nozzle portion of the rocket engine comprises a first frusto-conical section extending from said restricted throat and a second frusto-conical section forming a continuation of and attached to said first frusto-conical section.
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) | 1977-01-07 | 1977-07-09 | 1978-01-08 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-01-07 | 1981-07-09 | 1982-01-08 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-01-07 | 1985-07-09 | 1986-01-08 | $7700.00 | Window Closed / Lapsed |