US3861272A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Ammunition comprising a launcher tube and a reaction-driven missile
Assignee: Bayern Chemie Gesellschaft fuer Flugchemische Antriebe mbH
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Filing: 1972-12-13
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Granted: 1975-01-21
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Expires: 1992-12-13
Abstract
Abstract An ammunition construction for carriers, such as airplanes, comprises a launching tube which is adapted to be supported on the carrier and a missle which includes a front end portion which projects outwardly from the launching tube through a guide fin carrying tube section from the launching tube and a rear portion having a thrust drive engine which is supported in the launching tube. The launching tube includes a double walled formation defining a sealed annular space between the missle and the launching tube. The guide fin carrying tube includes projecting members distributed around its circumference which engage into guide grooves defined in the launching tube and the launching tube includes a holding ring having teeth which engage into recesses between the projections in order to ensure that no rotation takes place between the guide fin carrying tube and the launching tube.
Inventors
- 👤 Voler Koepfer
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-27 14:52
CPC Classifications
F; F41; F41F; F41F3/00; F41F3/04; F41F3/06
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
199 words
Ammunition for carriers, such as air planes, comprising a launching tube adapted to be supported on the carrier and having a launching end with an opening through which a missile is launched, a guide fin carrying tube section engaged with said launching tube and extending outwardly from said launching end, a missile having a rear thrust engine drive portion located within said launching tube and extending through said guide fin carrying tube section and terminating in a tip projecting outwardly from said section, means defining a closed space between said missile and said launching tube surrounding said drive engine for insulating said drive engine during carrying flight, means on said missile for lockably engaging said guide fin-carrying tube section as said missile is launched from said launching tube for combined flight of said guide fin-carrying tube section with said missile, said launching tube and said guide fin-carrying tube are telescopically engageable, a releasable plate mounted on said launching tube for temporarily locking said guide fin carrying tube section to said launching tube against axial movement in respect thereto, and projecting engagement means defined between said launching tube and said guide fin carrying tube section for preventing relative rotation therebetween.
Claim 2
Dependent Claim
199 words
Ammunition for carriers, such as air planes, comprising a launching tube adapted to be supported on the carrier and having a launching end with an opening through which a missile is launched, a guide fin carrying tube section engaged with said launching tube and extending outwardly from said launching end, a missile having a rear thrust engine drive portion located within said launching tube and extending through said guide fin carrying tube section and terminating in a tip projecting outwardly from said section, means defining a closed space between said missile and said launching tube surrounding said drive engine for insulating said drive engine during carrying flight, means on said missile for lockably engaging said guide fin-carrying tube section as said missile is launched from said launching tube for combined flight of said guide fin-carrying tube section with said missile, said launching tube and said guide fin-carrying tube are telescopically engageable, a releasable plate mounted on said launching tube for temporarily locking said guide fin carrying tube section to said launching tube against axial movement in respect thereto, and projecting engagement means defined between said launching tube and said guide fin carrying tube section for preventing relative rotation therebetween.
Claim 3
Dependent Claim
43 words
Ammunition for carriers, such as airplanes, according to claim 1, wherein said means for engaging said guide fin carrying tube section with said missile includes a projecting portion on said missile engageable in a recess portion on said guide fin carrying tube section.
Claim 4
Dependent Claim
118 words
Ammunition for carriers, such as airplanes, according to claim 1, including an annular sealing member disposed in said launching tube dimensioned to engage the wall of said missile and form a seal therewith adjacent the launching opening end thereof, and an opposite end having an inwardly extending projection of said launching tube forming a seal with said missile and closing the inner end of said launching tube, said missile being spaced inwardly from the interior wall of said launching tube at least at portions thereof which are sealed by said annular sealing member, and including an inwardly projecting portion of said launching tube engageable with the surface of said missile and sealing the inner end of said parts.
References Cited (Backward Citations)
US1257126A
Cited
US2344957A
Cited
US2792756A
Cited
US2961927A
Cited
US3110218A
Cited
US3440820A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1978-01-20 | 1978-07-22 | 1979-01-21 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-01-20 | 1982-07-22 | 1983-01-21 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-01-20 | 1986-07-22 | 1987-01-21 | $7700.00 | Window Closed / Lapsed |