US3711027A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Extendible nozzle for rocket engines
Assignee: Textron Inc
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Filing: 1971-03-17
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Granted: 1973-01-16
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Expires: 1991-03-17
Abstract
Abstract An improved rocket engine nozzle extension of the type that is deployable from a compactly ''''stowed'''' condition to an extended length condition; such as following a rocket stage separation so as to increase the engine thrust and therefore range-payload capabilities. The invention has particular relation to the problem of providing a reduced rocket engine length (when ''''stowed'''') in engines of the large expansion ratio nozzle type; for application in rocket vehicle upper stages, space-craft, envelope limited missiles, and the like. The disclosure features use of a frusto-cone-shaped member formed of thin and lightweight convoluted ductile sheet material, to comprise the engine nozzle wall structure which is adapted to be unrolled in crease-free manner. The device is arranged in combination with a temporary cover member which is so attached to the nozzle exit end portion thereof as to seal therein gas pressure sufficient to cause the nozzle structure to unroll into its extended configuration. The cover is then jettisoned so as to operatively open the nozzle.
Inventors
- 👤 L Carey
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 18:07
CPC Classifications
F; F02; F02K; F02K9/00; F02K9/97; F02K9/976
Claims Analysis
Total Claims: 20
Claim 1
Independent Claim
276 words
An extendible nozzle for a rocket engine comprising: a single, ductile, heat and erosion-resistant frusto-cone like sheet metal member being initially of convoluted form to define a first frusto-conical section having its smaller diameter end portion adapted to be permanently fixed to the exit port of a rocket engine to form a smooth divergent continuation of such exit port and to comprise the intake end of said nozzle, a frusto-conical terminal end portion comprising the discharge end of said nozzle and surrounding said first portion, and an intermediate portion of said member joining said first and terminal portions whereby the overall length dimension of said member is substantially less than the total of the length dimensions of said nozzle when extended, said intermediate portion comprising a reverse-directed frusto-conical member joined at its smaller diameter end to the larger diameter end of said first portion along a first circular fold line lying in a plane perpendicular to the axis of said first section and joined at its larger diameter end to the smaller diameter end of said terminal end portion along a second circular fold line also lying in a plane perpendicular to said axis and of larger diameter than said first fold line, and said intermediate portion defining a compression-resistant connection between said terminal end portion and said first portion to allow said terminal end portion to extend by unrolling of said second fold line only while such unrolling fold line seeks continually to remain in a plane perpendicular to said axis, and means for causing said member to unroll along said second fold line and to extend in smooth directional continuity throughout its extended length.
Claim 2
Dependent Claim
276 words
An extendible nozzle for a rocket engine comprising: a single, ductile, heat and erosion-resistant frusto-cone like sheet metal member being initially of convoluted form to define a first frusto-conical section having its smaller diameter end portion adapted to be permanently fixed to the exit port of a rocket engine to form a smooth divergent continuation of such exit port and to comprise the intake end of said nozzle, a frusto-conical terminal end portion comprising the discharge end of said nozzle and surrounding said first portion, and an intermediate portion of said member joining said first and terminal portions whereby the overall length dimension of said member is substantially less than the total of the length dimensions of said nozzle when extended, said intermediate portion comprising a reverse-directed frusto-conical member joined at its smaller diameter end to the larger diameter end of said first portion along a first circular fold line lying in a plane perpendicular to the axis of said first section and joined at its larger diameter end to the smaller diameter end of said terminal end portion along a second circular fold line also lying in a plane perpendicular to said axis and of larger diameter than said first fold line, and said intermediate portion defining a compression-resistant connection between said terminal end portion and said first portion to allow said terminal end portion to extend by unrolling of said second fold line only while such unrolling fold line seeks continually to remain in a plane perpendicular to said axis, and means for causing said member to unroll along said second fold line and to extend in smooth directional continuity throughout its extended length.
Claim 3
Dependent Claim
58 words
An extendible nozzle for a rocket engine as set forth in claim 1 wherein said means for causing said member to unroll comprises a cover and means temporarily attaching said cover to said larger diameter end portion so as to resist gas pressures thereagainst sufficient to remain connected to said end portion while forcing the member to unroll.
Claim 4
Dependent Claim
38 words
An extendible nozzle for a rocket engine as set forth in claim 2 wherein said means for causing said member to unroll includes a pressured gas supply means leading into the interior of said member and cover assembly.
Claim 5
Dependent Claim
29 words
An extendible nozzle for a rocket engine as set forth in claim 3 wherein said attachment means comprises spring fitted cooperating flange means on said member and cover respectively.
Claim 6
Dependent Claim
22 words
An extendible nozzle for a rocket engine as set forth in claim 3 wherein saiD attachment means includes an explosive disconnect device.
Claim 7
Dependent Claim
21 words
An extendible nozzle for a rocket engine as set forth in claim 3 wherein said attachment means comprises an adhesive substance.
Claim 8
Dependent Claim
32 words
An extendible nozzle for a rocket engine as set forth in claim 2 wherein said means for causing said member to unroll comprises the pressured gas discharge from the attached rocket engine.
Claim 9
Dependent Claim
26 words
An extendible nozzle for a rocket engine as set forth in claim 1 wherein said ductile and heat and erosion-resistant member is formed of ''''columbium C-103.''''
Claim 10
Dependent Claim
27 words
An extendible nozzle for a rocket engine as set forth in claim 1 wherein said member comprises a laminate including suitable ductile and heat and erosion-resistant materials.
Claim 11
Dependent Claim
24 words
An extendible nozzle for a rocket engine as set forth in claim 1 wherein said member comprises a ductile basis material coated with columbium.
Claim 12
Dependent Claim
29 words
An extendible nozzle for a rocket engine as set forth in claim 1 wherein said member comprises a ductile basis material coated with a ductile heat and erosion-resistant material.
Claim 13
Dependent Claim
258 words
An extendible nozzle for a rocket engine comprising: a single, ductile, heat and erosion-resistant frusto-cone like sheet metal member being initially of convoluted form to define an inner frusto-conical section having its smaller diameter end portion adapted to be permanently fixed to the exit port of a rocket engine to form a smooth divergent continuation of such exit port and to comprise the intake end of said nozzle, a frusto-conical terminal end portion thereof comprising the discharge end of said nozzle and in surrounding, parallel relation to said first portion, and an intermediate portion of said member joining said first and terminal portions whereby the overall length dimensions of said member is substantially less than the sum total of the length dimensions of said nozzle when extended, said intermediate portion comprising a reverse-directed frusto-conical member joined at its smaller diameter end to the larger diameter end of said first portion along a first circular fold line lying in a plane perpendicular to the axis of said first section and joined at its larger diameter end to the smaller diameter end of said terminal end portion along a second circular fold line also lying in a plane perpendicular to said axis and of larger diameter than said first fold line, and said intermediate portion defining a compression-resistant connection between said terminal end portion and said first portion to allow said terminal end portion to extend by unrolling of said second fold line only while such unrolling fold line seeks continually to remain in a plane perpendicular to said axis
Claim 14
Dependent Claim
258 words
An extendible nozzle for a rocket engine comprising: a single, ductile, heat and erosion-resistant frusto-cone like sheet metal member being initially of convoluted form to define an inner frusto-conical section having its smaller diameter end portion adapted to be permanently fixed to the exit port of a rocket engine to form a smooth divergent continuation of such exit port and to comprise the intake end of said nozzle, a frusto-conical terminal end portion thereof comprising the discharge end of said nozzle and in surrounding, parallel relation to said first portion, and an intermediate portion of said member joining said first and terminal portions whereby the overall length dimensions of said member is substantially less than the sum total of the length dimensions of said nozzle when extended, said intermediate portion comprising a reverse-directed frusto-conical member joined at its smaller diameter end to the larger diameter end of said first portion along a first circular fold line lying in a plane perpendicular to the axis of said first section and joined at its larger diameter end to the smaller diameter end of said terminal end portion along a second circular fold line also lying in a plane perpendicular to said axis and of larger diameter than said first fold line, and said intermediate portion defining a compression-resistant connection between said terminal end portion and said first portion to allow said terminal end portion to extend by unrolling of said second fold line only while such unrolling fold line seeks continually to remain in a plane perpendicular to said axis
Claim 15
Dependent Claim
26 words
An extendible nozzle for a rocket engine as set forth in claim 12 wherein said ductile and heat and erosion-resistant member is formed of ''''columbium C-103.''''
Claim 16
Dependent Claim
27 words
An extendible nozzle for a rocket engine as set forth in claim 12 wherein said member comprises a laminate including suitable ductile and heat and erosion-resistant materials.
Claim 17
Dependent Claim
24 words
An extendible nozzle for a rocket engine as set forth in claim 12 wherein said member comprises a ductile basis material coated with columbium.
Claim 18
Dependent Claim
29 words
An extendible nozzle for a rocket engine as set forth in claim 12 wherein said member comprises a ductile basis material coated with a ductile heat and erosion-resistant material.
Claim 19
Dependent Claim
234 words
In combination with a rocket engine of the type having a convergent section, a throat and a divergent section extending from the throat and terminating in an exit nozzle end of selected sectional area producing a fixed expansion ratio for the engine, a selectively extensible nozzle extension assembly for said rocket engine to increase said expansion ratio, said extension assembly comprising: a convoluted generally frusto-conical sheet metal member having at least two convolutions to define a first frusto-conical portion having a free end joined to said divergent section of the rocket engine and forming a smooth divergent continUation of and from said exit end thereof, a terminal frusto-conical portion nexted around said first portion and having a free end defining a supplemental exit nozzle having a sectional area substantially greater than the sectional area of said exit nozzle end of the rocket engine, and a reverse-directed frusto-conical intermediate portion between and joining said first and terminal portions, a cover member on the free end of said terminal portion to close off the supplemental exit nozzle thereof and to define a closed space within the rocket engine and extension assembly, and means detachably securing the cover member to said terminal portion for causing said convolutions to unroll in response to pressurization of said closed space and to deploy said portions into a divergent, smooth and crease-free extension of said divergent section of the rocket engine.
Claim 20
Dependent Claim
234 words
In combination with a rocket engine of the type having a convergent section, a throat and a divergent section extending from the throat and terminating in an exit nozzle end of selected sectional area producing a fixed expansion ratio for the engine, a selectively extensible nozzle extension assembly for said rocket engine to increase said expansion ratio, said extension assembly comprising: a convoluted generally frusto-conical sheet metal member having at least two convolutions to define a first frusto-conical portion having a free end joined to said divergent section of the rocket engine and forming a smooth divergent continUation of and from said exit end thereof, a terminal frusto-conical portion nexted around said first portion and having a free end defining a supplemental exit nozzle having a sectional area substantially greater than the sectional area of said exit nozzle end of the rocket engine, and a reverse-directed frusto-conical intermediate portion between and joining said first and terminal portions, a cover member on the free end of said terminal portion to close off the supplemental exit nozzle thereof and to define a closed space within the rocket engine and extension assembly, and means detachably securing the cover member to said terminal portion for causing said convolutions to unroll in response to pressurization of said closed space and to deploy said portions into a divergent, smooth and crease-free extension of said divergent section of the rocket engine.
References Cited (Backward Citations)
US3275193A
Cited
US3494513A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-01-16 | 1976-07-17 | 1977-01-16 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-01-16 | 1980-07-17 | 1981-01-16 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-01-16 | 1984-07-17 | 1985-01-16 | $7700.00 | Window Closed / Lapsed |