Patent US386306A successfully refreshed from Google Patents.
US3706281A
Expired / Lapsed
US
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Method and system for ejecting fairing sections from a rocket vehicle
Assignee: National Aeronautics and Space Administration
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Filing: 1971-04-01
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Granted: 1972-12-19
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Expires: 1991-04-01
Abstract
Abstract A method and system for deploying releasable clamshell fairing sections from a spinning rocket vehicle body, in which each fairing section is retained at its lower trailing edge portion, relative to the spin direction of the rocket, until it has been substantially despun and rotated outwardly from the rocket through a predetermined angle to thereby substantially eliminate the possibility of the fairing sections striking the vehicle payload. In a preferred constructional embodiment, a separable hinge unit is utilized connecting the lower trailing corner portion of each fairing section to the rocket vehicle body, whereby this portion will be the last to separate from the vehicle body and will be retained until the fairing section has rotated outwardly through the predetermined angle.
Inventors
- 👤 Lawrence F Hatakeyama
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 06:18
CPC Classifications
F; F42; F42B; F42B15/00; F42B15/36
Claims Analysis
Total Claims: 13
Claim 1
Independent Claim
89 words
A method for deploying releasable clamshell fairing sections from a spinning rocket vehicle body, comprising releasing the fairing sections from substantially their entire connection with the vehicle body; retaining the lower trailing edge portion of each fairing section with hinge means whose axis is substantially parallel to the spin axis of the rocket vehicle body, whereby each section will rotate outwardly from the vehicle body about the hinge means axis; and then releasing such lower trailing edge portions when the fairing sections have rotated outwardly through a predetermined angle.
Claim 2
Independent Claim
89 words
A method for deploying releasable clamshell fairing sections from a spinning rocket vehicle body, comprising releasing the fairing sections from substantially their entire connection with the vehicle body; retaining the lower trailing edge portion of each fairing section with hinge means whose axis is substantially parallel to the spin axis of the rocket vehicle body, whereby each section will rotate outwardly from the vehicle body about the hinge means axis; and then releasing such lower trailing edge portions when the fairing sections have rotated outwardly through a predetermined angle.
Claim 3
Dependent Claim
52 words
A method as defined in claim 1, wherein the fairing sections are initially further secured to each other at a location spaced from the connection with the vehicle body, further comprising releasing the fairing sections at said location from each other not later than release of the sections from the vehicle body.
Claim 4
Dependent Claim
26 words
A method as defined in claim 2, wherein the fairing sections are released from each other at said locations prior to release from the vehicle body.
Claim 5
Independent Claim
108 words
A system for deploying releasable clamshell fairing sections from a spinning rocket vehicle body, comprising first releasable securing means for releasably securing each of said sections to the rocket vehicle body; first releasing means for releasing said first securing means; and separable hinge means whose axis is substantially parallel to the spin axis of the rocket vehicle body for releasably securing the lower trailing edge portion of each section while permitting outward rotation of each section about the hinge means axis, following release of said first securing means, said separable hinge means being adapted to release its respective fairing section following outward rotation thereof through a predetermined angle.
Claim 6
Independent Claim
108 words
A system for deploying releasable clamshell fairing sections from a spinning rocket vehicle body, comprising first releasable securing means for releasably securing each of said sections to the rocket vehicle body; first releasing means for releasing said first securing means; and separable hinge means whose axis is substantially parallel to the spin axis of the rocket vehicle body for releasably securing the lower trailing edge portion of each section while permitting outward rotation of each section about the hinge means axis, following release of said first securing means, said separable hinge means being adapted to release its respective fairing section following outward rotation thereof through a predetermined angle.
Claim 7
Dependent Claim
55 words
A system as defined in claim 4 wherein said separable hinge means has a first part secured to the rocket vehicle body and a second part secured to the respective fairing section, said first and second parts being configured to separate from each other upon outward rotation of the fairing section through the predetermined angle.
Claim 8
Dependent Claim
111 words
A system as defined in claim 5, wherein said first part of said hinge means comprises first and second circumferentially spaced hinge members secured to the rocket vehicle body and respectively leading and trailing said second part of said hinge means, said second part having a leading edge and a trailing edge respectively abutting said first and second hinge members and a radially inwardly offset flange portion extending rearwardly and overlapping at least a portion of said second hinge member radially inwardly thereof, to thereby prevent linear radial outward movement of said second part and of the fairing section while permitting outward rotation thereof with respect to the rocket vehicle body.
Claim 9
Dependent Claim
58 words
A system as defined in claim 6, wherein said second part of said hinge means and said first hinge member comprise cooperating guide surfaces extending circumferentially relative to the vehicle body and restraining movement of said second part and clamshell member to rotation about said longitudinal axis, to thereby preclude yawing movement thereof relative to the vehicle body.
Claim 10
Dependent Claim
53 words
A system as defined in claim 7, wherein said leading edge of said second part of said hinge means further includes a curvilinear portion adapted for outward rolling movement relative to said first hinge member to facilitate the outward rotation of said second part and the fairing section relative to the vehicle body.
Claim 11
Dependent Claim
37 words
A system as defined in claim 8, further comprising third releasable securing means for releasably securing the fairing sections to each other at the forward ends thereof, and second releasing means for releasing said third securing means.
Claim 12
Dependent Claim
78 words
A system as defined in claim 9, wherein said firsT securing means comprises an open-ended band clamp surrounding the fairing sections and the rocket vehicle body, and pin means extending through the end of said band clamp and through one of the fairing sections; said third securing means comprises pin means extending through complementary joining portions of the fairing sections; and said first and second releasing means each comprise explosive pin-puller means for retracting their respective pin means.
Claim 13
Dependent Claim
49 words
A system as defined in claim 5, wherein said first and second parts of said separable hinge means comprise respective end portions of a frangible hinge strap member, said strap member being severable intermediate said end portions upon outward rotation of the respective fairing section through the predetermined angle.
References Cited (Backward Citations)
US3318241A
Cited
US3351013A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1975-12-19 | 1976-06-19 | 1976-12-19 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-12-19 | 1980-06-19 | 1980-12-19 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-12-19 | 1984-06-19 | 1984-12-19 | $7700.00 | Window Closed / Lapsed |