Solar power supply for spacecraft

Claim 3

The method of claim 1 wherein the step of affixing a portion of an electrically conductive wire mesh to said substrate comprises affixing a perimeter portion of said wire mesh to said substrate.

Claim 4

The method of claim 2 wherein the step of affixing a perimeter portion of said wire mesh to said substrate comprises positioning said wire mesh so as to span an aperture in said substrate, and affixing said perimeter portion of said wire mesh to said substrate circumjacent said aperture.

Claim 5

The method of claim 2 wherein the step of affixing a perimeter portion of said wire mesh to said substrate comprises stapling said perimeter portion of said wire mesh to said substrate.

Claim 6

The method of claim 2 wherein the step of affixing a perimeter portion of said wire mesh to said substrate comprises adhesively bonding said perimeter portion of said wire mesh to said substrate.

Claim 7

The method of claim 4 wherein the step of stapling said perimeter portion of said wire mesh to said substrate comprises stapling said perimeter portion to said substrate circumjacent an aperture in said substrate so that said wire mesh spans said aperture.

Claim 8

The method of claim 5 wherein the step of adhesively bonding a perimeter portion of said wire mesh to said substrate comprises adhesively bonding said perimeter portion to said substrate circumjacent an aperture in said substrate so that said wire mesh spans said aperture.

Claim 9

The method of claim 1 wherein the step of connecting an electrical terminal of each of said solar cells to said wire mesh comprises forming an electrically conductive joint between said electrical terminal and said wire mesh.

Claim 10

The method of claim 8 wherein the step of affixing a portion of said wire mesh to said substrate comprises affixing a perimeter portion of said wire mesh to said substrate circumjacent an aperture in said substrate so that said wire mesh spans said aperture.

Claim 11

The method of claim 1 comprising the further step of attaching said solar cells to said substrate by adhesive bonding means.

Claim 12

An electrical power supply comprising: (a) a substrate of flexible dielectric material; (b) a stress relieving electrically conductive wire mesh, a peripheral portion of said wire mesh being affixed to said substrate; and (c) a plurality of semiconductor devices for photovoltaic conversion of sunlight to electrical energy, each semiconductor device having an electrical terminal connected to said wire mesh.

Claim 13

An electrical power supply comprising: (a) a substrate of flexible dielectric material; (b) a stress relieving electrically conductive wire mesh, a peripheral portion of said wire mesh being affixed to said substrate; and (c) a plurality of semiconductor devices for photovoltaic conversion of sunlight to electrical energy, each semiconductor device having an electrical terminal connected to said wire mesh.

Claim 14

The electrical power supply of claim 11 wherein said peripheral portion of said wire mesh is affixed to said substrate circumjacent an aperture in said substrate so that said wire mesh spans said aperture.

Claim 15

The power supply of claim 12 wherein said substrate has first and second apertures, a first electrical terminal of each semiconductor device being electrically connected to a first wire mesh affixed to said substrate spanning said first aperture, and a second electrical terminal of each semiconductor device being electrically connected to a second wire mesh affixed to said substrate spanning said second aperture.

Claim 16

The power supply of claim 13 further comprising metallic traces formed on said substrate in a pattern defining circuit means for electrically connecting said wire meshes to connectors for coupling power generated by said semiconductor devices to an electrical load.

Claim 17

The power supply of claim 14 wherein said substrate has another plurality of semiconductor devices and third and fourth apertures, with third and fourth wire meshes being affixed to said substrate spanning said third and fourth apertures respectively, a first electrical terminal of each semiconductor device of said other plurality of semiconductor devices being electrically connected to the third wire mesh and a second electrical terminal of each semiconductor device of said other plurality of semiconductor devices being electrically connected to said fourth mesh, said pluralities of semiconductor devices being disposed in an array of parallel columns.

Claim 18

The power supply in claim 11 wherein said substrate is made of a sheet of polymeric material.

Claim 19

The power supply of claim 11 wherein said wire mesh is affixed to said substrate sheet by an adhesive bond.

Claim 20

The power supply of claim 11 wherein said wire mesh is affixed to said substrate sheet by stapling.

Claim 21

The power supply of claim 11 further comprising means for attaching said flexible substrate to a telescoping support structure that is extendible from a retracted position to a fully extended position, said substrate being foldable so as to assume a compact stowage configuration when said support structure is in said retracted position and to assume an elongate operational configuration when said support structure is in said fully extended position.

Claim 22

A solar power supply for a spacecraft, comprising a telescoping rigid support structure that is extendible from a retracted position to a fully extended position, a substrate sheet of flexible dielectric material attached to said telescoping support structure, said substrate sheet being foldable so as to assume a compact stowage configuration when said support structure is in said retracted position and to assume an elongate operational configuration when said support structure is in said fully extended position, said substrate sheet having first and second apertures, a first stress-relieving electrical conductor being affixed to said substrate sheet spanning said first aperture and a second stress-relieving electrical conductor being affixed to said substrate sheet spanning said second aperture, a plurality of semiconductor devices for photovoltaic conversion of sunlight to electrical energy, a first electrical terminal of each semiconductor device being electrically connected to said first stress-relieving electrical conductor and a second electrical terminal of each semiconductor device being electrically connected to said second stress-relieving electrical conductor, metallic traces being formed on said substrate sheet in a pattern defining circuit means for electrically connecting said first and second stress-relieving electrical conductors to connectors for coupling power from said semiconductor devices to an electrical load on said spacecraft.

Claim 23

A solar power supply for a spacecraft, comprising a telescoping rigid support structure that is extendible from a retracted position to a fully extended position, a substrate sheet of flexible dielectric material attached to said telescoping support structure, said substrate sheet being foldable so as to assume a compact stowage configuration when said support structure is in said retracted position and to assume an elongate operational configuration when said support structure is in said fully extended position, said substrate sheet having first and second apertures, a first stress-relieving electrical conductor being affixed to said substrate sheet spanning said first aperture and a second stress-relieving electrical conductor being affixed to said substrate sheet spanning said second aperture, a plurality of semiconductor devices for photovoltaic conversion of sunlight to electrical energy, a first electrical terminal of each semiconductor device being electrically connected to said first stress-relieving electrical conductor and a second electrical terminal of each semiconductor device being electrically connected to said second stress-relieving electrical conductor, metallic traces being formed on said substrate sheet in a pattern defining circuit means for electrically connecting said first and second stress-relieving electrical conductors to connectors for coupling power from said semiconductor devices to an electrical load on said spacecraft.

Claim 24

The spacecraft of claim 20 wherein said first and second stress-relieving electrical conductors are wire meshes.