Patent US3635425A successfully refreshed from Google Patents.
US3635425A
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US
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Deployment method for a telescoping solar array
Assignee: United States Department of the Navy
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Filing: 1969-10-01
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Granted: 1972-01-18
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Expires: 1989-10-01
Abstract
Abstract A method for deployment of a solar cell array, conduction of generated power from the array to the satellite, and utilization of the array and deployment means as an aid for the gravitygradient stabilization of the satellite. The method envisions telescoping sections of a solar cell array being extended in orbit by an erectable mast and boom assembly. Power is carried from the array through electrically conductive booms and twin conducting masts, thereby eliminating the need for electrical wiring and associated wiring guides and connectors. The extended solar array also assists in stabilizing the satellite by providing necessary gravity-gradient restoring moments. Multiple function of equipment increases the wattage to weight ratio of the array.
Inventors
- 👤 Charles J Swet
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 17:28
CPC Classifications
B; B64; B64G; B64G1/00; B64G1/22; B64G1/42; B64G1/44; B64G1/443; B64G1/222; B64G1/2221; B64G1/2226; B64G1/24; B64G1/34; Y; Y10; Y10S; Y10S136/00; Y10S136/291; Y10S136/292
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
96 words
In a space vehicle, a method for deployment of a radiation responsive array having telescoping sections on which solar cell panels are disposed, the sections being stowable within a reduced volume in concentric relation, an outer section housing inner sections arranged mutually concentrically therein, comprising; joining deployment means to the outer section of the array; joining the innermost section of the array to the main body of the spacecraft; and extending the deployment means to pull the concentric inner sections from their stowed positions within the outer section, thereby exposing said sections to incident solar radiation.
Claim 2
Dependent Claim
96 words
In a space vehicle, a method for deployment of a radiation responsive array having telescoping sections on which solar cell panels are disposed, the sections being stowable within a reduced volume in concentric relation, an outer section housing inner sections arranged mutually concentrically therein, comprising; joining deployment means to the outer section of the array; joining the innermost section of the array to the main body of the spacecraft; and extending the deployment means to pull the concentric inner sections from their stowed positions within the outer section, thereby exposing said sections to incident solar radiation.
Claim 3
Dependent Claim
25 words
The method of claim 1, and further comprising conducting power generated by the array from the array to tHe space vehicle through the mast itself.
Claim 4
Dependent Claim
23 words
The method of claim 1, and further comprising stabilizing the space vehicle by damping moments occurring on extension of the mast and array.
Claim 5
Dependent Claim
113 words
A deployable solar array for a spacecraft comprising; deployment means mounted on the spacecraft, said means having a free end extendible from the spacecraft on deployment thereof; a solar panel assembly including telescoping arcuate frame sections, each section having semicylindrical solar panels held thereon, the sections being of sequentially reduced dimensions to permit telescoping mating of said sections; said panel assembly having an inner telescoping section releasably joined to the spacecraft and an outer telescoping section joined to the free end of the deployment means; said deployment means on spatial extension of the free end thereof from the spacecraft pulling out the telescoping sections of the solar panel assembly to deploy said assembly.
Claim 6
Dependent Claim
113 words
A deployable solar array for a spacecraft comprising; deployment means mounted on the spacecraft, said means having a free end extendible from the spacecraft on deployment thereof; a solar panel assembly including telescoping arcuate frame sections, each section having semicylindrical solar panels held thereon, the sections being of sequentially reduced dimensions to permit telescoping mating of said sections; said panel assembly having an inner telescoping section releasably joined to the spacecraft and an outer telescoping section joined to the free end of the deployment means; said deployment means on spatial extension of the free end thereof from the spacecraft pulling out the telescoping sections of the solar panel assembly to deploy said assembly.
Claim 7
Dependent Claim
36 words
The deployable solar array of claim 4, wherein said deployment means include longitudinally extendable boom means mounted on the spacecraft for spatial extension therefrom along a direction normal to the base line of said deployment means.
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) | 1975-01-17 | 1975-07-19 | 1976-01-18 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-01-17 | 1979-07-19 | 1980-01-18 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-01-17 | 1983-07-19 | 1984-01-18 | $7700.00 | Window Closed / Lapsed |