Patent US4451017A successfully refreshed from Google Patents.
US4451017A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Three stage rocket vehicle with parallel staging
Assignee: National Aeronautics and Space Administration
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Filing: 1982-09-30
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Granted: 1984-05-29
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Expires: 2002-09-30
Abstract
Abstract A three stage rocket vehicle (11) having a large forward propellant tank (12) and a small aft propellant tank (13) axially aligned. Secured to the rear end of the aft propellant tank (13) is an engine mount structure (14) carrying rocket engines (15). Offset and secured to the propellant tanks (12,13) is a payload structure (18). The propellants from the large forward tank (12) are fed into the aft propellant tank (13) and the rocket engines (15) are fed propellants from the aft propellant tank (13). This arrangement enables the vehicle to parallel stage its use of engines and components.
Inventors
- 👤 William R. Marshall
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 23:08
CPC Classifications
B; B64; B64G; B64G1/00; B64G1/002; B64G1/22; B64G1/40; B64G1/402; B64G1/4022; B64G1/64; B64G1/641; B64G1/401
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
278 words
A three-stage rocket launch vehicle having a propellant feed system from a forward tank stage to an aft tank stage, comprising: axially aligned forward and aft tanks for carrying propellants for rocket engines; an intertank structure fixedly joined to the front portion of said aft tank and severably joined to the rear portion of said forward tank; an engine mount structure secured to the rear portion of said aft propellant tank; at least one rocket engine supported by said engine mount structure; a pair of solid rocket boosters secured to opposed sides of said forward and aft propellant tanks; said forward propellant tank having a front pressure vessel for carrying hydrogen and a rear pressure vessel for carrying oxygen; said aft tank having a front pressure vessel for carrying hydrogen and a rear pressure vessel for carrying oxygen; a first pipe line communicating said front pressure vessels, and a second pipe line communicating said rear pressure vessels for feeding propellants from the front pressure vessels to said rear pressure vessels as propellant is provided from said rear pressure vessels to said at least one rocket engine; each said first and second pipe lines having on-command shut-off valves and joint means for severing the pipe line on-command; third and fourth pipe lines communicating, respectively, said forward vessel and said rear vessel of said aft propellant tank with said at least one rocket engine supported by said engine support structure; and an elongated payload structure severably fixed to the third side of said forward propellant tank and fixed to the third side of said aft propellant tank, said payload structure extending parallel to said forward and said aft propellant tanks.
Claim 2
Dependent Claim
278 words
A three-stage rocket launch vehicle having a propellant feed system from a forward tank stage to an aft tank stage, comprising: axially aligned forward and aft tanks for carrying propellants for rocket engines; an intertank structure fixedly joined to the front portion of said aft tank and severably joined to the rear portion of said forward tank; an engine mount structure secured to the rear portion of said aft propellant tank; at least one rocket engine supported by said engine mount structure; a pair of solid rocket boosters secured to opposed sides of said forward and aft propellant tanks; said forward propellant tank having a front pressure vessel for carrying hydrogen and a rear pressure vessel for carrying oxygen; said aft tank having a front pressure vessel for carrying hydrogen and a rear pressure vessel for carrying oxygen; a first pipe line communicating said front pressure vessels, and a second pipe line communicating said rear pressure vessels for feeding propellants from the front pressure vessels to said rear pressure vessels as propellant is provided from said rear pressure vessels to said at least one rocket engine; each said first and second pipe lines having on-command shut-off valves and joint means for severing the pipe line on-command; third and fourth pipe lines communicating, respectively, said forward vessel and said rear vessel of said aft propellant tank with said at least one rocket engine supported by said engine support structure; and an elongated payload structure severably fixed to the third side of said forward propellant tank and fixed to the third side of said aft propellant tank, said payload structure extending parallel to said forward and said aft propellant tanks.
Claim 3
Dependent Claim
71 words
A three-stage rocket launch vehicle according to claim 1, wherein: said engine mount structure has a first part fixed to the rear portion of said aft propellant tank, and a second part severably secured to said aft propellant tank; a plurality of main rocket engines supported by said second part of the engine mount structure and a single main rocket engine supported by said first part of the engine mount structure.
Claim 4
Dependent Claim
42 words
A three-stage rocket launch vehicle according to claim 1 wherein: said payload carrying structure is a spacecraft having three main rocket engines and the propellant of said aft propellant tank is also fed to said three main rocket engines of the spacecraft.
Claim 5
Dependent Claim
125 words
A method of placing a three-stage rocket launch vehicle according to claim 2 in orbit, comprising: at stage-one, firing said pair of solid rocket boosters and said plurality of main rocket engines until the depletion of said solid rocket boosters and then jettisoning said solid rocket boosters aside; at stage-two firing said main rocket engines until the depletion of said forward propellant tank and then jettisoning said forward propellant tank, and said second part of said engine mount structure with its said plurality of main rocket engines; at stage-three, continuing to fire said single main rocket engine supported by said first part of the engine mount structure utilizing the propellant from the aft propellant tank so as to place the remaining vehicle components into orbit.
Claim 6
Dependent Claim
128 words
A method of placing a three-stage rocket launch vehicle according to claim 3 in orbit, comprising: at stage-one, firing said pair of solid rocket boosters and said three main rocket engines and said at least one rocket engine until the depletion of said solid rocket boosters, and then jettisoning said solid rocket boosters aside; at stage-two firing said three main rocket engines and said at least one rocket engine until depletion of said forward propellant tank, and then jettisoning said forward propellant tank aside, and shutting off said three main engines on said spacecraft; at stage-three, continuing to fire said at least one rocket engine supported by said engine mount structure utilizing the propellant from the aft propellant tank until orbit of the remaining vehicle components is achieved.
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) | 1987-05-29 | 1987-11-28 | 1988-05-29 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1991-05-29 | 1991-11-28 | 1992-05-29 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1995-05-29 | 1995-11-28 | 1996-05-29 | $7700.00 | Window Closed / Lapsed |