US3735948A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Rocket catapult
Assignee: US AS REPRESENTED BY SECRETARY
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Filing: 1971-06-01
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Granted: 1973-05-29
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Expires: 1991-06-01
Abstract
Abstract A rocket catapult ejection arrangement for a seat-occupant mass of a disabled aircraft in which the longitudinal axis through the nozzle throat of the rocket motor is always operatively directed toward the center of gravity of the seat-occupant mass regardless of individual seat elevational adjustments affected for any of various flight condition improvements.
Inventors
- 👤 H D Macdonald
- 👤 N J Waecker
- 👤 C S Sterrett
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 11:52
CPC Classifications
B; B64; B64D; B64D25/00; B64D25/08; B64D25/10
Claims Analysis
Total Claims: 13
Claim 1
Independent Claim
181 words
In a rocket catapult eJection system for a seat-occupant mass of an aircraft having rocket motor means attached at one end to an aircraft seat structure, and carrying a unidirectionally tiltable nozzle member at the other end, said seat-occupant mass having a predetermined center of gravity for elevationally adjusted positions of said aircraft seat structure, said nozzle being tiltable in a plane containing all of said center of gravity locations, said rocket motor means having a rearwardly located nozzle housing having transversely extending trunnion means rotatably supporting said nozzle member, said nozzle member having a coordinately contoured protruding abutment surface, adjustable stop means rotatably mounted on said nozzle housing and having a stop surface of predetermined contour extending in the path of said nozzle abutment surface, said stop means including a cylindrical sleeve portion having a cam follower track of predetermined angular contour for receiving a protruding lug of said seat structure, so constructed and arranged that longitudinal movement of said lug in elevational adjustment of said seat will rotate said track sleeve and impart rotational adjustment of said stop surface.
Claim 2
Dependent Claim
181 words
In a rocket catapult eJection system for a seat-occupant mass of an aircraft having rocket motor means attached at one end to an aircraft seat structure, and carrying a unidirectionally tiltable nozzle member at the other end, said seat-occupant mass having a predetermined center of gravity for elevationally adjusted positions of said aircraft seat structure, said nozzle being tiltable in a plane containing all of said center of gravity locations, said rocket motor means having a rearwardly located nozzle housing having transversely extending trunnion means rotatably supporting said nozzle member, said nozzle member having a coordinately contoured protruding abutment surface, adjustable stop means rotatably mounted on said nozzle housing and having a stop surface of predetermined contour extending in the path of said nozzle abutment surface, said stop means including a cylindrical sleeve portion having a cam follower track of predetermined angular contour for receiving a protruding lug of said seat structure, so constructed and arranged that longitudinal movement of said lug in elevational adjustment of said seat will rotate said track sleeve and impart rotational adjustment of said stop surface.
Claim 3
Dependent Claim
14 words
The structure in accordance with claim 1 wherein said track is of spiral configuration.
Claim 4
Dependent Claim
20 words
The structure of claim 2 wherein the track is a right hand spiral having a helix angle of substantially 15*.
Claim 5
Dependent Claim
71 words
The structure according to claim 3 wherein said adjustable stop means includes an arcuate segmental clip member having a grooved undersurface in matingly slidable position on a lateral surface of said nozzle housing, and a rearward surface including a separate pair of face angle portions, and a relieved surface portion having a bevel angle of substantially 45* relative to a plane transverse to the longitudinal axis of said rocket motor means.
Claim 6
Dependent Claim
42 words
The structure of claim 4 wherein said clip rearward surface has a lead of substantially 2.9 inches and a helix angle of substantially 70*, so constructed and arranged that when said seat is elevated the permitted angle of nozzle rotation is reduced.
Claim 7
Dependent Claim
45 words
The structure of claim 5 wherein said clip face angle surface portions extend at respective angles of substantially 18* and 30* relative to said transverse plane, and the outer surface of said clip has a tapped hole for threaded connection of said sleeve portion thereto.
Claim 8
Dependent Claim
57 words
The structure of claim 6 wherein said nozzle abutment surface has a face angle surface portion having an angle of substantially 27* relative to a plane transverse to the throat longitudinal axis of said nozzle and a compound face and helix angle surface portion having respective angles of substantially 27* and 18* relative to said transverse plane.
Claim 9
Dependent Claim
57 words
The structure of claim 1 wherein said nozzle abutment surface has a face angle surface portion having an angle of substantially 27* relative to a plane transverse to the throat longitudinal axis of said nozzle and a compound face and helix angle surface portion having respective angles of substantially 27* and 18* relative to said transverse plane.
Claim 10
Dependent Claim
70 words
The structure according to claim 1 wherein said adjustable stop means include an arcuate segmental clip member having a grooved undersurface in matingly slidable position on a lateral surface of said nozzle housing, and a rearward surface including a separate pair of face angle portions, and a relieved surface portion having a bevel angle of substantially 45* relative to plane transverse to the longitudinal axis of said rocket motor means.
Claim 11
Dependent Claim
42 words
The structure of claim 9 wherein said clip rearward surface has a lead of substantially 2.9 inches and a helix angle of substantially 70*, so constructed and arranged that when said seat is elevated the permitted angle of nozzle rotation is reduced.
Claim 12
Dependent Claim
45 words
The structure of claim 10 wherein said clip face angle surface portions extend at respectIve angles of substantially 18* and 30* relative to said transverse plane, and the outer surface of said clip has a tapped hole for threaded connection of said sleeve portion thereto.
Claim 13
Dependent Claim
56 words
The structure of claim 11 wherein said nozzle abutment surface has a face angle surface portion having angle of substantially 27* relative to a plane transverse to the throat longitudinal axis of said nozzle and a compound face and helix angle surface portion having respective angles of substantially 27* and 18* relative to said transverse plane.
References Cited (Backward Citations)
US3282161A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-05-28 | 1976-11-27 | 1977-05-29 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-05-28 | 1980-11-27 | 1981-05-29 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-05-28 | 1984-11-27 | 1985-05-29 | $7700.00 | Window Closed / Lapsed |