Patent US3946639A successfully refreshed from Google Patents.
US3946639A
Expired / Lapsed
US
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Fin and spin stabilized rocket
Assignee: DRS Sustainment Systems Inc
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Filing: 1974-09-06
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Granted: 1976-03-30
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Expires: 1994-09-06
Abstract
Abstract A weapon system is provided with a projectile incorporating improvements which reduce launching errors. In the preferred embodiment, the projectile is a rocket. The rocket is spin stabilized by gyroscopic force and a condition of nearly neutral aerodynamic stability is provided by the external rocket contour. In the preferred embodiment, the rocket is spin stabilized in flight by a forward fin ring and a rearward aerodynamic, flared skirt. The skirt includes a bearing ring structure which supports the rocket within a launcher vehicle or tube along the rearward portion of the rocket body. The fin ring constitutes a second projectile support during launch and is positioned along the forward portion of the projectile body. The projectile and its associated launcher vehicle are configured to eliminate tip off error. Both the bearing ring structure and fin ring are journaled to the projectile to permit rotation of the projectile body. The fin and bearing rings each have means integrally formed with them for spring loading the projectile within its launch vehicle prior to launch. Spring loading the projectile reduces mal aim launch errors during projectile firing.
Inventors
- 👤 Francis A. Sanvito
- 👤 Allen L. Pearson
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 02:42
CPC Classifications
F; F42; F42B; F42B10/00; F42B10/02; F42B10/26; F42B10/28; F42B10/30; F41; F41F; F41F3/00; F41F3/04
Claims Analysis
Total Claims: 25
Claim 1
Independent Claim
239 words
A projectile system, which comprises: launcher means; a fin and spin stabilized projectile carried by said launcher means, said projectile including: an elongated cylindrical body having a forward portion and a rearward portion, said rearward portion including a flared, aerodynamic skirt having a larger circumference than said forward portion of said projectile, said skirt including a bearing ring structure forming a part of said skirt, said bearing ring structure defining an outermost diametric part of said skirt, and including means for permitting free rotation of said projectile along said bearing ring structure, the bearing ring structure portion of said skirt comprising a rearward support for said projectile during launch; propulsion means carried by said rearward portion for propelling said projectile along a flight path to a target; means, carried by said projectile for rotating said projectile about its longitudinal axis for spin stabilizing said projectile during flight; and a plurality of symmetrically arranged and rotationally free aerodynamic fin means carried by said projectile for guiding said projectile along a flight path to a target, said fin means comprising a second projectile support during launch, individual ones of said fin means plurality having an open mouth channel formed in it near the radially outward end of said fin means, said channel having a first width portion and a second, materially different width portion, the smallest of said first and second width portions forming the open mouth part of said channel.
Claim 2
Dependent Claim
239 words
A projectile system, which comprises: launcher means; a fin and spin stabilized projectile carried by said launcher means, said projectile including: an elongated cylindrical body having a forward portion and a rearward portion, said rearward portion including a flared, aerodynamic skirt having a larger circumference than said forward portion of said projectile, said skirt including a bearing ring structure forming a part of said skirt, said bearing ring structure defining an outermost diametric part of said skirt, and including means for permitting free rotation of said projectile along said bearing ring structure, the bearing ring structure portion of said skirt comprising a rearward support for said projectile during launch; propulsion means carried by said rearward portion for propelling said projectile along a flight path to a target; means, carried by said projectile for rotating said projectile about its longitudinal axis for spin stabilizing said projectile during flight; and a plurality of symmetrically arranged and rotationally free aerodynamic fin means carried by said projectile for guiding said projectile along a flight path to a target, said fin means comprising a second projectile support during launch, individual ones of said fin means plurality having an open mouth channel formed in it near the radially outward end of said fin means, said channel having a first width portion and a second, materially different width portion, the smallest of said first and second width portions forming the open mouth part of said channel.
Claim 3
Dependent Claim
52 words
The projectile system of claim 1 wherein said bearing ring structure comprises a housing including a bearing mounting area, a flexible diaphragm portion, and a hoop spring separated from said bearing mounting area by said diaphragm portion, said hoop being resiliently deflectable and defining said rearward support for said projectile during launch.
Claim 4
Dependent Claim
22 words
The projectile system of claim 2 wherein the housing of said bearing ring structure has silhouette shaped in plan as a frustum.
Claim 5
Dependent Claim
41 words
The projectile system of claim 3 wherein the outboard tip of individual ones of said fin plurality is canted so that the radially outermost part of individual ones of said fin means is near the open mouth part of said channel.
Claim 6
Dependent Claim
197 words
In a rocket system including a smooth bore, projectile bearing tube, a plurality of supports spaced about a periphery of and attached to said tube, said supports and said smooth bore tube defining first and second tube sections delineated by first and second internal diameters, and a projectile carried by said tube prior to launch, the improvement which comprises means for spring loading said projectile in said tube during prelaunch actuation of said projectile, said spring loading means comprising a first self-contained projectile support comprising a first support means journaled for rotation with respect to said projectile and attached thereto along a rearward portion of said projectile, said first support means including means for spring loading said projectile in said tube, and a second self-contained projectile support comprising a plurality of symmetrically arranged and rotationally free aerodynamic fins carried by said forward portion of said projectile body, each of said fin plurality including means for spring loading said projectile in said tube, said projectile being adapted to be carried by said tube such that said first projectile support rests in said first tube internal diameter and said second projectile support rests in said second tube internal diameter.
Claim 7
Dependent Claim
197 words
In a rocket system including a smooth bore, projectile bearing tube, a plurality of supports spaced about a periphery of and attached to said tube, said supports and said smooth bore tube defining first and second tube sections delineated by first and second internal diameters, and a projectile carried by said tube prior to launch, the improvement which comprises means for spring loading said projectile in said tube during prelaunch actuation of said projectile, said spring loading means comprising a first self-contained projectile support comprising a first support means journaled for rotation with respect to said projectile and attached thereto along a rearward portion of said projectile, said first support means including means for spring loading said projectile in said tube, and a second self-contained projectile support comprising a plurality of symmetrically arranged and rotationally free aerodynamic fins carried by said forward portion of said projectile body, each of said fin plurality including means for spring loading said projectile in said tube, said projectile being adapted to be carried by said tube such that said first projectile support rests in said first tube internal diameter and said second projectile support rests in said second tube internal diameter.
Claim 8
Dependent Claim
85 words
The improvement of claim 5 wherein each of said fins has an open mouth channel formed in it near the radially outward end of said fin, said channel having a first width portion and a second width portion, the smallest of said first and said second width portions forming the open mouth portion of said channel, the portion of said fin outboard of said channel defining a spring, said spring comprising said means for spring loading said projectile in said tube for said fin plurality.
Claim 9
Dependent Claim
85 words
The improvement of claim 6 wherein said projectile includes an elongated cylindrical body having a forward portion and a rearward portion, said fin plurality being carried by said projectile along said forward portion, said rearward portion including a flared, aerodynamic skirt having a larger circumference than said forward portion of said projectile, said skirt including a bearing ring structure defining the outermost diametric portion of said skirt, said bearing ring structure permitting free rotation of said projectile and further constituting said first self-contained projectile support.
Claim 10
Dependent Claim
58 words
The improvement of claim 7 wherein said bearing ring structure comprises a housing including a bearing mounting area, a flexible diaphragm portion, and a hoop spring separated from said bearing mounting area by said diaphragm portion, said hoop spring being resiliently deflectable for spring loading said projectile in said tube along the rearward portion of said projectile body.
Claim 11
Dependent Claim
45 words
The improvement of claim 8 wherein the distance between the rearward ends of said fin plurality and the forward end of said tube is equal to the distance between the rearward end of said bearing ring structure and the forward end of said support plurality.
Claim 12
Dependent Claim
217 words
A combination fin and spin stabilized projectile and launcher therefor, which comprises: an elongated projectile body having a forward portion and a rearward portion, said rearward portion including a first projectile support attached to said projectile and journaled with respect thereto so as to permit rotation of said projectile, said first projectile support including means for exerting a radial spring force between said projectile and a projectile bearing tube; propulsion means carried by said projectile for propelling said projectile along a flight path to a target; means for rotating said projectile about its longitudinal axis for spin stabilizing said projectile during flight; a plurality of symmetrically arranged and rotationally free aerodynamic fin means carried by said projectile for guiding said projectile along a flight path to a target, said fin means comprising a second projectile support during launch, said fin means including means for exerting a radial spring force between said projectile and a projectile bearing tube; an open ended projectile bearing tube; and at least two supports spaced about the inner periphery of said tube so as to define first and second tube sections delineated by first and second internal diameters and arranged so that said first projectile support rests in said first internal diameter and said second projectile support rests in said second internal diameter.
Claim 13
Dependent Claim
217 words
A combination fin and spin stabilized projectile and launcher therefor, which comprises: an elongated projectile body having a forward portion and a rearward portion, said rearward portion including a first projectile support attached to said projectile and journaled with respect thereto so as to permit rotation of said projectile, said first projectile support including means for exerting a radial spring force between said projectile and a projectile bearing tube; propulsion means carried by said projectile for propelling said projectile along a flight path to a target; means for rotating said projectile about its longitudinal axis for spin stabilizing said projectile during flight; a plurality of symmetrically arranged and rotationally free aerodynamic fin means carried by said projectile for guiding said projectile along a flight path to a target, said fin means comprising a second projectile support during launch, said fin means including means for exerting a radial spring force between said projectile and a projectile bearing tube; an open ended projectile bearing tube; and at least two supports spaced about the inner periphery of said tube so as to define first and second tube sections delineated by first and second internal diameters and arranged so that said first projectile support rests in said first internal diameter and said second projectile support rests in said second internal diameter.
Claim 14
Dependent Claim
114 words
The combination of claim 10 wherein said fin means comprises a ring surrounding said projectile with four fins spaced 90° about said ring and extending radially outwardly therefrom, said ring being journaled to said body for relative rotation with respect thereto, each of said fins having a proximal end attached to said ring and a distal end extending radially outwardly therefrom, individual ones of said fin means having an open mouth channel formed in it near the radially outward end of said fin, said channel having a first width portion and a materially different second width portion, the smallest of said first and said second width portions forming the open mouth of said channel.
Claim 15
Dependent Claim
62 words
The combination of claim 11 wherein said first projectile support includes a bearing ring structure having a housing, said housing including a bearing mounting area, a flexible diaphragm portion, and a hoop spring separated from said bearing mounting area by said diaphragm portion, said hoop spring being resiliently deflectable so as to permit insertion of said projectile in said projectile bearing tube.
Claim 16
Dependent Claim
44 words
The combination as set forth in claim 12 wherein the internal diameter of said first and said second tube sections are less than the effective outer diameter of said first and said second projectile supports prior to insertion of said projectile in said tube.
Claim 17
Dependent Claim
45 words
The combination of claim 13 wherein the distance between the rearward edge of said fin means and the forward end of said tube is equal to the distance between the rearward end of said first projectile support and the forward end of said spaced supports.
Claim 18
Dependent Claim
137 words
In a weapons system including a launcher vehicle having a bore for receiving a projectile, said bore having first and second sections delineated by first and second internal diameters, and a projectile carried by said launcher vehicle prior to launch, the improvement which comprises means for spring loading said projectile in said bore so as to permit diametric movement by said projectile with respect to said bore, said spring loading means comprising a first self-contained projectile support for supporting said projectile along said first bore section, and a second projectile support for supporting said second bore section, each of said first and said second supports including means for spring loading said projectile with respect to said launcher vehicle, said launcher vehicle and said projectile being isolated from one another except along said first and said second supports.
Claim 19
Dependent Claim
137 words
In a weapons system including a launcher vehicle having a bore for receiving a projectile, said bore having first and second sections delineated by first and second internal diameters, and a projectile carried by said launcher vehicle prior to launch, the improvement which comprises means for spring loading said projectile in said bore so as to permit diametric movement by said projectile with respect to said bore, said spring loading means comprising a first self-contained projectile support for supporting said projectile along said first bore section, and a second projectile support for supporting said second bore section, each of said first and said second supports including means for spring loading said projectile with respect to said launcher vehicle, said launcher vehicle and said projectile being isolated from one another except along said first and said second supports.
Claim 20
Dependent Claim
48 words
The improvement of claim 15 wherein said projectile includes an elongated body having a forward portion and a rearward portion, said rearward portion including a flared aerodynamic skirt and a bearing support structure forming a portion of said skirt, said bearing support structure defining said second projectile support.
Claim 21
Dependent Claim
42 words
The improvement of claim 16 wherein said bearing support structure includes a housing having a bearing mounting area, a flexible diaphragm portion and spring means separated from said bearing mounting area by said flexible diaphragm portion, said spring means being resiliently deflectable.
Claim 22
Dependent Claim
20 words
The improvement of claim 17 wherein the housing of said bearing support structure is shaped as a frustum in plan.
Claim 23
Dependent Claim
87 words
The improvement of claim 15 wherein said first projectile support comprises a plurality of symmetrically arranged, rotationally free aerodynamic fin means carried by said projectile for guiding said projectile along a flight path to a target, individual ones of said fin means plurality having an open mouth channel formed in them near their radially outward extremity, said channel having a first width portion and a substantially different second width portion, the smaller of said first and said second width portions forming the open mouth of said channel.
Claim 24
Dependent Claim
35 words
The improvement of claim 19 wherein the tip of each of said fin means is canted so that the radially outermost part of said fin means is near the open mouth part of said channel.
Claim 25
Dependent Claim
36 words
The improvement of claim 19 wherein the first section of said bore includes means for preventing angular rotation of said fin means, said rotation preventing means comprising a plurality of rails extending longitudinally of said bore.
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) | 1979-03-30 | 1979-09-29 | 1980-03-30 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1983-03-30 | 1983-09-29 | 1984-03-30 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1987-03-30 | 1987-09-29 | 1988-03-30 | $7700.00 | Window Closed / Lapsed |