US4467985A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Vortex inhibiting closed spherical outlet structure
Assignee: The AT&T MVPD Group LLC
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Filing: 1982-09-29
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Granted: 1984-08-28
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Expires: 2002-09-29
Abstract
Abstract Spherical tank 30 has its outlet 34 angularly positioned away from the tank center line axis 54 which is parallel to the local gravity vector 26. This angular positioning of outlet 34 inhibits vortexing as liquid is withdrawn from tank 30.
Inventors
- 👤 Jeremiah O. Salvatore
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 12:02
CPC Classifications
B; B64; B64D; B64D37/00; B64D37/02; B64D37/06; B64G; B64G1/00; B64G1/22; B64G1/40; B64G1/402; B64G1/4022; Y; Y10; Y10T; Y10T137/00; Y10T137/8593; Y10T137/86348
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
196 words
A closed spherical tank for mounting in a spin-stabilized spacecraft for the storage and discharge of propellant liquid in a space environment having a gravity vector due to the spinning of the spacecraft, said tank comprising: a closed spherical tank shell having a center point and enclosing an unobstructed spherical tank interior volume for the containment of propellant liquid, said tank having an axis through the center of said tank and in line with the local gravity vector caused by the spinning of the spacecraft, the improvement comprising: said closed spherical tank of unobstructed interior having an outlet comprising an opening in said closed spherical shell and an outlet tube connected to said opening and extending out of said opening and not into said shell to provide a completely open unobstructed interior in said shell, said outlet tube being for discharging propellant liquid from said closed spherical shell of said tank; said outlet being between 1° and 15° angularly away from said spherical tank center line axis in line with the local gravity vector caused by spinning of the spacecraft to inhibit vortexing in propellant liquid being discharged from said spherical tank out of said outlet.
Claim 2
Dependent Claim
196 words
A closed spherical tank for mounting in a spin-stabilized spacecraft for the storage and discharge of propellant liquid in a space environment having a gravity vector due to the spinning of the spacecraft, said tank comprising: a closed spherical tank shell having a center point and enclosing an unobstructed spherical tank interior volume for the containment of propellant liquid, said tank having an axis through the center of said tank and in line with the local gravity vector caused by the spinning of the spacecraft, the improvement comprising: said closed spherical tank of unobstructed interior having an outlet comprising an opening in said closed spherical shell and an outlet tube connected to said opening and extending out of said opening and not into said shell to provide a completely open unobstructed interior in said shell, said outlet tube being for discharging propellant liquid from said closed spherical shell of said tank; said outlet being between 1° and 15° angularly away from said spherical tank center line axis in line with the local gravity vector caused by spinning of the spacecraft to inhibit vortexing in propellant liquid being discharged from said spherical tank out of said outlet.
Claim 3
Dependent Claim
17 words
The tank of claim 1 wherein said outlet is between 5° and 10° away from said axis.
Claim 4
Dependent Claim
153 words
A closed spherical tank for mounting on a spin-stabilized spacecraft for containing propellant liquid and for use where the local gravity vector is caused by stabilizing spin of the spacecraft, said spherical tank comprising: a closed shell enclosing the spherical tank volume in which propellant liquid is to be stored, said shell being spherical and having a center and having an axis passing through the center of said tank and directed parallel to the local gravity vector, the improvement comprising: said closed spherical tank having a completely unobstructed interior, an outlet in said shell and an outlet tube fastened to extend away from said outlet from said spherical shell for discharging propellant liquid from the unobstructed interior of said spherical shell, said outlet tube not extending into said shell to provide a completely open shell interior; and said outlet from said spherical shell being positioned between 5° and 10° away from said axis.
Claim 5
Dependent Claim
153 words
A closed spherical tank for mounting on a spin-stabilized spacecraft for containing propellant liquid and for use where the local gravity vector is caused by stabilizing spin of the spacecraft, said spherical tank comprising: a closed shell enclosing the spherical tank volume in which propellant liquid is to be stored, said shell being spherical and having a center and having an axis passing through the center of said tank and directed parallel to the local gravity vector, the improvement comprising: said closed spherical tank having a completely unobstructed interior, an outlet in said shell and an outlet tube fastened to extend away from said outlet from said spherical shell for discharging propellant liquid from the unobstructed interior of said spherical shell, said outlet tube not extending into said shell to provide a completely open shell interior; and said outlet from said spherical shell being positioned between 5° and 10° away from said axis.
Claim 6
Dependent Claim
111 words
In a system for delivery of liquid fuel to a combustor for use on a spin-stabilized satellite wherein a closed fuel tank has a gravitational axis caused by satellite spin, a spherical surface of revolution about such axis, a completely unobstructed tank interior and an outlet for propellant liquid fuel flowing from said tank, a method for inhibiting the ingestion, into the propellant liquid fuel withdrawn through said outlet, of gas from an axial vortex within said closed tank, the method comprising the steps of positioning said outlet away from said gravitational axis at the lower end thereof by 1°-15° and then withdrawing said propellant liquid fuel from said positioned outlet.
Claim 7
Dependent Claim
111 words
In a system for delivery of liquid fuel to a combustor for use on a spin-stabilized satellite wherein a closed fuel tank has a gravitational axis caused by satellite spin, a spherical surface of revolution about such axis, a completely unobstructed tank interior and an outlet for propellant liquid fuel flowing from said tank, a method for inhibiting the ingestion, into the propellant liquid fuel withdrawn through said outlet, of gas from an axial vortex within said closed tank, the method comprising the steps of positioning said outlet away from said gravitational axis at the lower end thereof by 1°-15° and then withdrawing said propellant liquid fuel from said positioned outlet.
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) | 1987-08-28 | 1988-02-27 | 1988-08-28 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1991-08-28 | 1992-02-27 | 1992-08-28 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1995-08-28 | 1996-02-27 | 1996-08-28 | $7700.00 | Window Closed / Lapsed |