Patent US3749334A successfully refreshed from Google Patents.
US3749334A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Attitude compensating missile system
Assignee: United States Department of the Army
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Filing: 1966-04-04
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Granted: 1973-07-31
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Expires: 1986-04-04
Abstract
Abstract A missile utilizing directional control guidance concepts in which torques proportional to missile attitude are generated to correct attitude of the missile during its flight to impact at a target.
Inventors
- 👤 W Mccorkle
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 07:33
CPC Classifications
F; F41; F41G; F41G7/00; F41G7/34; F41G7/36; F42; F42B; F42B10/00; F42B10/60; F42B10/66
Claims Analysis
Total Claims: 18
Claim 1
Independent Claim
210 words
A directional control system for maintaining a missile on a launch predetermined path comprising: a. a gyroscope mounted with its spin axis and rotor aligned with the longitudinal axis of the missile at launch, said missile moveable transaxially relative to said rotor; b. at least three substantially equally spaced and radially aligned ports mounted on the missile in communication with the atmosphere; c. a source of pressurized fluid carried by said gyro rotor for providing a reaction force on said rotor which is proportional to the reaction force acting on said missile as a result of the thrust developed therein; d. a jet nozzle disposed in concentric alignment with said spin axes of said gyro rotor and in communication with said ports for directing said pressurized fluid along the spin axis of said rotor whereby reaction of the expelled pressurized fluid from said rotor through said concentric nozzle provides a reaction force on said gyro to impart an acceleration thereto substantially equal to the missile acceleration to provide for unrestricted movement of said gyro. e. said gyroscope having said rotor operatively connected between said source and said ports for providing a variable fluid flow therethrough to provide balancing forces to the missile responsive to its movement relative to said rotor.
Claim 2
Dependent Claim
210 words
A directional control system for maintaining a missile on a launch predetermined path comprising: a. a gyroscope mounted with its spin axis and rotor aligned with the longitudinal axis of the missile at launch, said missile moveable transaxially relative to said rotor; b. at least three substantially equally spaced and radially aligned ports mounted on the missile in communication with the atmosphere; c. a source of pressurized fluid carried by said gyro rotor for providing a reaction force on said rotor which is proportional to the reaction force acting on said missile as a result of the thrust developed therein; d. a jet nozzle disposed in concentric alignment with said spin axes of said gyro rotor and in communication with said ports for directing said pressurized fluid along the spin axis of said rotor whereby reaction of the expelled pressurized fluid from said rotor through said concentric nozzle provides a reaction force on said gyro to impart an acceleration thereto substantially equal to the missile acceleration to provide for unrestricted movement of said gyro. e. said gyroscope having said rotor operatively connected between said source and said ports for providing a variable fluid flow therethrough to provide balancing forces to the missile responsive to its movement relative to said rotor.
Claim 3
Dependent Claim
20 words
A missile as in claim 1 wherein said attitude reference device is disposed forwardly of the missile center of gravity.
Claim 4
Dependent Claim
114 words
A missile as in claim 2 wherein said gyroscope comprises: a. a bearing housing secured to the frame of said missile and having a plurality of bearings therein and a rotor shaft mounted in said bearings and extending from said housing; b. a casing secured to said rotor shaft for rotation therewith and defining said rotor, said casing having a combustion charge mounted therein to form said source of pressurized fluid; c. actuating means for initiating rotational movement of said casing; d. means for igniting said combustion charge for rotation of said casing and said rotor shaft; and, e. means for securing said housing to the frame of said missile in gimballed relation thereto.
Claim 5
Dependent Claim
77 words
A missile as in claim 3 wherein said actuating means comprises: a. an annular member disposed about the periphery of said casing; b. propellant means carried in a chamber provided in said annular member and disposed for ignition to provide propulsive gases for initial rotation of said casing; c. a plurality of nozzles disposed peripherally about said annular member and in communication with said chamber to exhaust said propulsive gases therefrom for the rotation of said casing.
Claim 6
Dependent Claim
64 words
A missile as in claim 4 including: a. caging means for securing said housing against movement prior to initiation of rotational movement of said rotor by said actuating means and for release of said housing to permit unrestrained movement thereof subsequent to initiation of said rotational movement by said actuating means; and, b. means for energizing said caging means for release of said housing.
Claim 7
Dependent Claim
103 words
A missile as in claim 1 wherein said gyroscope comprises: a. A hOllow shaft secured to the frame of said missile; b. a rotor shaft rotatably mounted in said hollow shaft in gimballed relation thereto and extending therefrom; c. a casing secured to said rotor shaft for rotation therewith and defining said rotor, said casing having said combustion charge therein; d. drive means releasably secured to said casing for imparting initial rotation thereto, said drive means disposed for release of said casing for unrestrained movement thereof and for imparting spin to the missile for spin stabilization thereof subsequent to release of said casing.
Claim 8
Dependent Claim
18 words
A missile as in claim 6 wherein said gyroscope is disposed forwardly of the missile center of gravity.
Claim 9
Dependent Claim
65 words
A missile as in claim 7 wherein said drive means comprises: a. an annular drive member mounted concentrically about said hollow shaft for rotation; b. actuating means for rotating said annular drive member; c. braking means carried by said annular drive member for engagement with the frame of said missile for imparting said spin to said missile responsive to rotation of said annular drive member.
Claim 10
Dependent Claim
88 words
A missile as in claim 8 including: a. a support member disposed for support of said hollow shaft and extending therefrom in biased relation with the frame of said missle; and b. movable means disposed for movement along the length of said support member responsive to rotation of said drive member. c. means coacting with said movable means and said annular drive member for release thereof from said casing and for moving said brake means into the engagement with the missile frame for imparting spin to said missile.
Claim 11
Dependent Claim
70 words
A missile as in claim 9 wherein said actuating means comprises: a. a combustible charge carried in an annular chamber in said annular drive member and disposed for ignition to provide propulsive gases for rotation of said member; b. a plurality of nozzles disposed about the periphery of said annular member and in communication with said chamber to exhaust said propulsive gases therefrom for the rotation of said drive member.
Claim 12
Dependent Claim
151 words
A missile as in claim 10 wherein a. said support member is provided with a cylindrical configuration having external screw threads thereon; b. said means coacting with said movable means includes a nut mounted on said support member in threaded relation therewith; c. a plurality of pins carried in said nut and extending into slots provided on the inner periphery of said annular drive member for rotation thereby and movement along said support member responsive to rotation of said drive member, said pins disposed for engagement with said annular drive member responsive to a predetermined length of travel of said nut on said support member for movement of said drive member along the longitudinal axis of said missile for release and uncaging of said gyro wheel, said pins disposed for continued movement of said annular drive member until said brake means engages the frame of said missile to impart spin thereto.
Claim 13
Dependent Claim
81 words
A missile as in claim 11 including: a. a plurality of flat springs mounted on an end surface of said annular drive member and in biased engagement with said casing for retention thereof in the caged position; b. a plurality of pins mounted in slots provided in said surface of said annular drive member for insertion in correspondingly spaced slots provided on said casing to provide the releasable connection between said drive member and said casing for the initial rotation thereof.
Claim 14
Dependent Claim
68 words
A missile as in claim 12 including: a. a plurality of ports disposed about the periphery of said missile for exhausting propulsive gases of said drive member actuating means to the atmosphere; b. a member carried by said annular drive member for movement therewith along the longitudinal axis of said missile to seal off said ports at completion of burning of said combustion charge of said drive member.
Claim 15
Dependent Claim
127 words
A missile as in claim 13 wherein said control means comprises: A. a nozzle secured to said casing in axial alignment with the longitudinal axis of said missile and said rotor shaft, said nozzle having a plurality of ports disposed around the periphery thereof in communication with the interior of said casing and nozzle; and, b. said passage means including a plurality of channels secured to the frame of said missile in communication with the exit of said nozzle and the atmosphere, said channels being concentrically disposed about said nozzle and joining at a point along the longitudinal axis of said missile and said nozzle for equal distribution of said combustion gases through each of said channels when the axes of said reference and said missile coincide.
Claim 16
Dependent Claim
198 words
A missile disposed for flight in a trajectory ending in a target comprising: a. propulsion means carried by said missile for propelling said missile to a target; b. mechanism carried by said missile for retention thereof in the trajectory, said mechanism including a space oriented attitude reference device having a gyro wheel provided with a combustion charge therein disposed for ignition for providing thrust producing gases for rotating said gyro wheel; and, control means including a plurality of passages communicating with said gyro wheel and the atmosphere for directing said thrust producing gases to the atmosphere through predetermined ones of said passages for providing restoring torques on said missile for restoration of said missile in the trajectory responsive to deviations therefrom; c. caging means for securing said gyro wheel against movement prior to rotational movement thereof and for release of said gyro wheel to permit unrestrained rotational movement thereof, said caging means including a housing having a piston slidably mounted therein, detent means disposed on said piston for supporting the gyrorotor in a caged position, and means for actuating said piston for movement thereof for release of the gyrorotor to an uncaged position to permit unrestrained movement thereof.
Claim 17
Dependent Claim
198 words
A missile disposed for flight in a trajectory ending in a target comprising: a. propulsion means carried by said missile for propelling said missile to a target; b. mechanism carried by said missile for retention thereof in the trajectory, said mechanism including a space oriented attitude reference device having a gyro wheel provided with a combustion charge therein disposed for ignition for providing thrust producing gases for rotating said gyro wheel; and, control means including a plurality of passages communicating with said gyro wheel and the atmosphere for directing said thrust producing gases to the atmosphere through predetermined ones of said passages for providing restoring torques on said missile for restoration of said missile in the trajectory responsive to deviations therefrom; c. caging means for securing said gyro wheel against movement prior to rotational movement thereof and for release of said gyro wheel to permit unrestrained rotational movement thereof, said caging means including a housing having a piston slidably mounted therein, detent means disposed on said piston for supporting the gyrorotor in a caged position, and means for actuating said piston for movement thereof for release of the gyrorotor to an uncaged position to permit unrestrained movement thereof.
Claim 18
Dependent Claim
128 words
A missile as in claim 15 wherein said control means comprises: a. a nozzle secured to said casing in axial alignment with the longitudinal axis of said missile and said rotor shaft, said nozzle having a plurality of ports disposed around the periphery thereof in communication with the interior of said casing and nozzle; and, b. said passage means including a plurality of channels secured to the frame of said missile in communication with the exit of said nozzle and the atmosphere, said channels being concentrically disposed about said nozzle and joining at a point along the longitudinal axis of said missile and said nozzle for equal distribution of said combustion gases through each of said channels when the axes of said reference device and said missile coincide.
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) | 1976-07-30 | 1977-01-29 | 1977-07-31 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-07-30 | 1981-01-29 | 1981-07-31 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-07-30 | 1985-01-29 | 1985-07-31 | $7700.00 | Window Closed / Lapsed |