US3857320A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Node suspended flexible rocket
Assignee: United States Department of the Army
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Filing: 1973-01-29
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Granted: 1974-12-31
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Expires: 1993-01-29
Abstract
Abstract This invention relates to modifying a fairly conventional spin stabilized rocket by locating the bearings which support the spinning rocket at the nodes of the primary bending mode of the round. This structure allows higher spin rates than with current designs by reducing the sensitivity of the round to spin-induced bending.
Inventors
- 👤 R Conard
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 16:50
CPC Classifications
F; F41; F41F; F41F3/00; F41F3/04; F41F3/048
Claims Analysis
Total Claims: 2
Claim 1
Independent Claim
188 words
In combination with a launch tube having a rear smaller diameter portion and a forward larger diameter portion, a spin stabilized missile having two ball bearing assemblies mounted thereon, each of said bearing assemblies comprising an inner and an outer race and a series of balls therebetween, the inner race of the rearmost bearing assembly being mounted on said missile at the rear bending node of the missile and the outer race bearing against the wall of the smaller diameter rear portion of said launcher, a plurality of longitudinally extending slotted rails mounted in the forward larger diameter portion of said launcher, the inner race of the forward bearing assembly being mounted on said missile at the forward bending node of said missile, fins attached to the outer race of said forward bearing assembly and slideably received in the slots in said rails, whereby the support being at the node points wherein there is no movement relative to said launcher the missile principal longitudinal axis of inertia will remain coincident with the longitudinal axis of the launcher regardless of any bending of the missile induced by rotation thereof.
Claim 2
Dependent Claim
188 words
In combination with a launch tube having a rear smaller diameter portion and a forward larger diameter portion, a spin stabilized missile having two ball bearing assemblies mounted thereon, each of said bearing assemblies comprising an inner and an outer race and a series of balls therebetween, the inner race of the rearmost bearing assembly being mounted on said missile at the rear bending node of the missile and the outer race bearing against the wall of the smaller diameter rear portion of said launcher, a plurality of longitudinally extending slotted rails mounted in the forward larger diameter portion of said launcher, the inner race of the forward bearing assembly being mounted on said missile at the forward bending node of said missile, fins attached to the outer race of said forward bearing assembly and slideably received in the slots in said rails, whereby the support being at the node points wherein there is no movement relative to said launcher the missile principal longitudinal axis of inertia will remain coincident with the longitudinal axis of the launcher regardless of any bending of the missile induced by rotation thereof.
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) | 1977-12-30 | 1978-07-01 | 1978-12-31 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-12-30 | 1982-07-01 | 1982-12-31 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-12-30 | 1986-07-01 | 1986-12-31 | $7700.00 | Window Closed / Lapsed |