Patent US4609169A successfully refreshed from Google Patents.
US4609169A
Expired / Lapsed
US
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Propellant tank resupply system
Assignee: United States, UNITED STATES AIR FORCE, Secretary of
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Filing: 1984-08-14
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Granted: 1986-09-02
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Expires: 2004-08-14
Abstract
Abstract A novel propellant resupply system for, and method of recharging the propellant tanks of, the attitude control system (ACS) of a spacecraft or the like are described, comprising first and second propellant conduits respectively interconnecting the outlets of the fuel and oxidizer pump inducers of the primary propulsion system with the fuel and oxidizer tanks for the ACS thruster engines, and controller valves within each propellant conduit for controllably diverting fuel and oxidizer under pressure from the fuel and oxidizer pumps to the thruster fuel and oxidizer tanks during operation of the primary propulsion system engines.
Inventors
- 👤 Thomas F. Schweickert
- 👤 George F. Orton
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-27 20:36
CPC Classifications
B; B64; B64G; B64G1/00; B64G1/22; B64G1/40; B64G1/402; B64G1/24; B64G1/26; Y; Y10; Y10T; Y10T137/00; Y10T137/4673
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
216 words
In an attitude control system for a spacecraft or the like having a primary propulsion system including at least one primary engine, a source of fuel and a source of oxidizer, and separate fuel pump means and oxidizer pump means for pressurizing fuel and oxidizer for burning in said at least one primary engine, said attitude control system including at least one thruster engine and a pressurized fuel supply tank and a pressurized oxidizer supply tank for supplying fuel and oxidizer to said thruster engine, an improvement, comprising: a. first conduit means operatively connected at one end to the outlet of said fuel pump means and at the other end to the thruster engine fuel supply tank; b. second conduit means operatively connected at one end to the outlet of said oxidizer pump means and at the other end to the thruster engine oxidizer supply tank; and c. control valve means within each said first and second conduit means for controllably diverting, respectively, fuel and oxidizer under pressure from said fuel and oxidizer pump means to said thruster engine fuel and oxidizer supply tanks during operation of said at least one primary engine whereby the thruster engine fuel and oxidizer supply tanks are resupplied under pressure during said operation of said at least one primary engine.
Claim 2
Dependent Claim
216 words
In an attitude control system for a spacecraft or the like having a primary propulsion system including at least one primary engine, a source of fuel and a source of oxidizer, and separate fuel pump means and oxidizer pump means for pressurizing fuel and oxidizer for burning in said at least one primary engine, said attitude control system including at least one thruster engine and a pressurized fuel supply tank and a pressurized oxidizer supply tank for supplying fuel and oxidizer to said thruster engine, an improvement, comprising: a. first conduit means operatively connected at one end to the outlet of said fuel pump means and at the other end to the thruster engine fuel supply tank; b. second conduit means operatively connected at one end to the outlet of said oxidizer pump means and at the other end to the thruster engine oxidizer supply tank; and c. control valve means within each said first and second conduit means for controllably diverting, respectively, fuel and oxidizer under pressure from said fuel and oxidizer pump means to said thruster engine fuel and oxidizer supply tanks during operation of said at least one primary engine whereby the thruster engine fuel and oxidizer supply tanks are resupplied under pressure during said operation of said at least one primary engine.
Claim 3
Dependent Claim
22 words
The improvement as recited in claim 1 wherein said fuel pump means and said oxidizer pump means each comprises a turbopump inducer.
Claim 4
Dependent Claim
23 words
The improvement recited in claim 1 wherein said source of fuel and said source of oxidizer comprise, respectively, monomethyl hydrazine and nitrogen tetroxide.
Claim 5
Independent Claim
222 words
A method for recharging the propellant tanks of an attitude control system of a spacecraft or the like having a primary propulsion system including at least one primary engine, a source of fuel and a source of oxidizer, and separate fuel pump means and oxidizer pump means for pressurizing fuel and oxidizer for burning in said at least one primary engine, said attitude control system including at least one thruster engine and a pressurized fuel supply tank and pressurized oxidizer supply tank for supplying fuel and oxidizer to said thruster engine, said method comprising the steps of: a. providing first and second conduit means, said first conduit means operatively connected at one end to the outlet of said fuel pump means and at the other end to the thruster engine fuel supply tank, and said second conduit means operatively connected at one end to the outlet of said oxidizer pump means and at the other end to the thruster engine oxidizer supply tank; and b. controllably diverting fuel and oxidizer, respectively, through said first and second conduit means from said fuel pump means and said oxidizer pump means to the thruster fuel and oxidizer supply tanks during operation of said primary engine whereby the thruster engine fuel and oxidizer supply tanks are recharged under pressure during said operation of said primary engine.
Claim 6
Independent Claim
222 words
A method for recharging the propellant tanks of an attitude control system of a spacecraft or the like having a primary propulsion system including at least one primary engine, a source of fuel and a source of oxidizer, and separate fuel pump means and oxidizer pump means for pressurizing fuel and oxidizer for burning in said at least one primary engine, said attitude control system including at least one thruster engine and a pressurized fuel supply tank and pressurized oxidizer supply tank for supplying fuel and oxidizer to said thruster engine, said method comprising the steps of: a. providing first and second conduit means, said first conduit means operatively connected at one end to the outlet of said fuel pump means and at the other end to the thruster engine fuel supply tank, and said second conduit means operatively connected at one end to the outlet of said oxidizer pump means and at the other end to the thruster engine oxidizer supply tank; and b. controllably diverting fuel and oxidizer, respectively, through said first and second conduit means from said fuel pump means and said oxidizer pump means to the thruster fuel and oxidizer supply tanks during operation of said primary engine whereby the thruster engine fuel and oxidizer supply tanks are recharged under pressure during said operation of said primary engine.
Claim 7
Dependent Claim
22 words
The method as recited in claim 4 wherein said fuel pump means and said oxidizer pump means each comprises a turbopump inducer.
Claim 8
Dependent Claim
23 words
The method recited in claim 4 wherein said source of fuel and said source of oxidizer comprise, respectively, monomethyl hydrazine and nitrogen tetroxide.
References Cited (Backward Citations)
US3097480A
Cited
US2818915A
Cited
US3756024A
Cited
US3231223A
Cited
US3231224A
Cited
US3369771A
Cited
US3537669A
Cited
US3977633A
Cited
US4288051A
Cited
US4451017A
Cited
FR2537544A1
Cited
US4505124A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1989-09-01 | 1990-03-03 | 1990-09-02 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1993-09-01 | 1994-03-03 | 1994-09-02 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1997-09-01 | 1998-03-03 | 1998-09-02 | $7700.00 | Window Closed / Lapsed |