US3645475A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Fluid amplifier with direct-coupled gyrocontrol
Assignee: United States Department of the Army
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Filing: 1969-12-01
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Granted: 1972-02-29
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Expires: 1989-12-01
Abstract
Abstract A large power-flueric amplifier is controlled by selective restriction of opposing control parts. An inertially stabilized wheel serves to orifice the amplifier control ports to generate a control moment for directional control of a rocket or missile. A hot gas generator furnishes output gases that exhaust through the fluid amplifier, exiting through opposing exhaust ports around the periphery of the missile to maintain the missile on the original flight path. The inertially stabilized wheel, spinning in a plane normal to the missile flight path, spins on a sleeve or bearing through which the nozzle of the flueric amplifier passes. Tubular members extend radially from the flueric amplifier interaction chamber and terminate adjacent the interior annular surface of the spinning wheel. The wheel covers a portion of each tube inlet and varies the opening of each control inlet in response to relative motion between the spinning wheel and the missile. Ambient air pressure at each control inlet is constantly applied to uniformly exhausting gases when the missile is aligned with the spinning gyrowheel. Deviation in missile direction results in increased ambient pressure at one control port and decreased pressure at the opposing control port, causing the exhaust gases to move toward one wall, thus, producing an imbalance in the exhaust port gases which restore the missile to the flight path.
Inventors
- 👤 William W Stripling
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-07 11:43
CPC Classifications
F; F42; F42B; F42B10/00; F42B10/60; F42B10/66
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
179 words
A large power-flueric amplifier comprising: a means for producing a stream of fluid at a uniform rate of flow, a chamber housing having an input port connected to receive said fluid stream and having a plurality of evenly spaced output ports for exhausting said fluid therethrough, at least three control ports projecting from said chamber around the periphery thereof in a plane normal to the longitudinal axis of said chamber for varying the surface pressure on said fluid stream, gyro control means adjacent to and partially covering said control ports for increasing and decreasing the opening to said control ports in response to deviation of said chamber housing from a fixed line of reference with said control means for controlling the direction of fluid flow through said outlets to return the chamber housing to said line of reference, and said gyro control means having a spinning wheel rotating on a sleeve or bearing that surrounds a portion of said chamber housing, the inner surface of said wheel covering at least a portion of the opening of said control ports.
Claim 2
Dependent Claim
179 words
A large power-flueric amplifier comprising: a means for producing a stream of fluid at a uniform rate of flow, a chamber housing having an input port connected to receive said fluid stream and having a plurality of evenly spaced output ports for exhausting said fluid therethrough, at least three control ports projecting from said chamber around the periphery thereof in a plane normal to the longitudinal axis of said chamber for varying the surface pressure on said fluid stream, gyro control means adjacent to and partially covering said control ports for increasing and decreasing the opening to said control ports in response to deviation of said chamber housing from a fixed line of reference with said control means for controlling the direction of fluid flow through said outlets to return the chamber housing to said line of reference, and said gyro control means having a spinning wheel rotating on a sleeve or bearing that surrounds a portion of said chamber housing, the inner surface of said wheel covering at least a portion of the opening of said control ports.
Claim 3
Dependent Claim
71 words
A fluid amplifier as set forth in claim 1 wherein each of said exhaust ports include a tubular passageway forming member extending radially from said housing chamber in a plane perpendicular to the axis of said chamber and spaced evenly apart for exhausting a balancing fluid flow therefrom only when the spin axis of said spinning wheel coincides with the longitudinal axis of said chamber for maintaining said axes in coincidence.
Claim 4
Dependent Claim
74 words
A fluid amplifier as set forth in claim 2 wherein said fluid producing means is a gas generator and said fluid is the exhaust gas of said generator, said output ports comprise first, second, third and fourth output ports for said fluid that are radially spaced 90* apart, and said control ports include first, second, third and fourth control ports having chamber openings longitudinally adjacent said first, second, third and fourth output ports respectively.
Claim 5
Dependent Claim
150 words
In a guided missile, an attitude control system for maintaining the missile on a predetermined launch path comprising an elongated chamber housing having a fixed longitudinal axis thereof aligned with the longitudinal axis of said missile and having an input port at one end thereof and a plurality of exhaust ports at the other end thereof, a gas generator having an output thereof connected to said chamber input for directing a uniform flow of exhaust gas therethrough to exit through said exhaust ports, direct-coupled control means adjacent said chamber housing having a reference axis in parallel with the chamber longitudinal axis prior to missile launch, and a plurality of chamber control ports having openings in said chamber adjacent said exhaust ports, and responsive tO axial changes between said chamber and said control means for varying the surface pressure applied to said exhaust gas flowing through said chamber after missile launch.
Claim 6
Dependent Claim
150 words
In a guided missile, an attitude control system for maintaining the missile on a predetermined launch path comprising an elongated chamber housing having a fixed longitudinal axis thereof aligned with the longitudinal axis of said missile and having an input port at one end thereof and a plurality of exhaust ports at the other end thereof, a gas generator having an output thereof connected to said chamber input for directing a uniform flow of exhaust gas therethrough to exit through said exhaust ports, direct-coupled control means adjacent said chamber housing having a reference axis in parallel with the chamber longitudinal axis prior to missile launch, and a plurality of chamber control ports having openings in said chamber adjacent said exhaust ports, and responsive tO axial changes between said chamber and said control means for varying the surface pressure applied to said exhaust gas flowing through said chamber after missile launch.
Claim 7
Dependent Claim
87 words
An attitude control system as set forth in claim 4 wherein said chamber housing is a proportional fluid amplifier, said exhaust ports are 4 tubular passageway forming members equally spaced about the chamber longitudinal axis for connecting said chamber to the external surface of said missile for exhausting said gas therethrough to control the direction of missile flight, said ports intersecting said missile surface in a plane perpendicular to the missile flight axis to produce uniform thrust therefrom when said missile is on said predetermined launch path.
Claim 8
Dependent Claim
91 words
An attitude control system as set forth in claim 5 wherein said direct-coupled control means is a gyro having a spinning wheel rotating on a sleeve or bearing around the periphery of said chamber housing adjacent said control ports, said spinning wheel having an inner surface edge covering at least a portion of the opening of each control port for varying ambient pressure applied therethrough a restore said missile to said flight path when the missile deviates from said flight path, and wherein said reference axis is the gyro spin axis.
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) | 1975-02-28 | 1975-08-30 | 1976-02-29 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-02-28 | 1979-08-30 | 1980-02-29 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-02-28 | 1983-08-30 | 1984-02-29 | $7700.00 | Window Closed / Lapsed |