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An energy storage arrangement wherein electrical charge is stored in capacitor elements dispersed throughout, for example, surface structural components of an aircraft. The electrical capacitor elements may involve dielectric material-separated electrical plates comprising the aircraft skin or prefe

An energy storage arrangement wherein electrical charge is stored in capacitor elements dispersed throughout, for example, surface structural components of an aircraft. The electrical capacitor elements may involve dielectric material-separated electrical plates comprising the aircraft skin or preferably may involve numerous wire-like cylindrical capacitor elements dispersed within the weaving of the hardened fabric materials used to fabricate the aircraft. Other elements of the aircraft including internal structure and divider members may also be included in the energy storage function. Pulsed use of the stored energy in, for example, directed energy weapons devices are a contemplated application of the invention. The invention may be viewed as a combined employment of aircraft components in both structural and energy storing functions thus enabling a reduction in aircraft payload utilization and space consumption.

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We claim: 1. The weight conserving and space conserving method of capacitively storing electrical energy within the enclosure of an aircraft airframe, said method comprising the steps of: fabricating substantial portions of said airframe from structural materials comprised of intimately spaced elec

We claim: 1. The weight conserving and space conserving method of capacitively storing electrical energy within the enclosure of an aircraft airframe, said method comprising the steps of: fabricating substantial portions of said airframe from structural materials comprised of intimately spaced electrically isolated and electrical capacitance-comprising first and second electrical conductors disposed in a woven fabric; connecting a plurality of said first electrical conductors to a first common electrical node; joining a plurality of said second electrical conductors to a second common electrical node; disposing an electrical capacitance charging electrical potential between said first and second electrical nodes at a capacitor charging rate. 2. The weight conserving and space conserving method of capacitively storing electrical energy within the enclosure of an aircraft airframe of claim 1 further including the step of fabricating said structural materials as a woven fabric matrix of carbonaceous fibers. 3. The weight conserving and space conserving method of capacitively storing electrical energy within the enclosure of an aircraft airframe of claim 2 further including the step of dispersing a plurality of concentrically disposed electrical conductor pair electrical capacitor elements in said fabric matrix of carbonaceous fibers. 4. The weight conserving and space conserving method of capacitively storing electrical energy within the enclosure of an aircraft airframe of claim 2 further including the step of dispersing said plurality of concentrically disposed electrical conductor pair electrical capacitor elements along one of a warp axis and a weave axis of said fabric matrix of carbonaceous fibers. 5. The weight conserving and space conserving method of capacitively storing electrical energy within the enclosure of an aircraft airframe of claim 1 further including the step of withdrawing electrical energy accompanying said electrical potential from an electrical capacitance comprised of said node connected and node joined intimately spaced electrically isolated and electrical capacitance-comprising first and second electrical conductors during a repetitive cycle of capacitance charging and discharging events. 6. The weight conserving and space conserving method of capacitively storing electrical energy within the enclosure of an aircraft airframe of claim 1 wherein said aircraft is a military aircraft and said repetitive cycle of capacitance charging and discharging events comprise a firing and re-energizing cycle of a directed energy weapon carried by said aircraft. 7. The weight conserving and space conserving method of capacitively storing electrical energy within the enclosure of an aircraft airframe of claim 1 wherein said aircraft airframe comprises one of an atmospheric supported winged aircraft, a spacecraft, and a watercraft. 8. The weight conserving and space conserving method of capacitively storing electrical energy within the enclosure of an aircraft airframe of claim 1 further including the step of: removing said stored electrical energy from said charged electrical capacitance at a rate faster than said capacitor charging rate. 9. The weight conserving and space conserving method of capacitively storing electrical energy within the enclosure of an aircraft airframe of claim 8 further including the step of continuing said charging and removing events in a repeating energy dissipating cycle. 10. The weight conserving and space conserving method of capacitively storing electrical energy within the enclosure of an aircraft airframe of claim 1 wherein said step of fabricating substantial portions of said airframe from structural materials comprised of intimately spaced electrically isolated and electrical capacitance-comprising first and second electrical conductors disposed in a woven fabric includes one of: bonding a metal foil to a dielectric coated wire, electro-less plating a dielectric coated wire, flame spraying a metal coating over a dielectric coated wire and dispersing, by one of spray, vapor deposit and painting, a metal coating over a dielectric coated wire. 11. The weight conserving and space conserving method of capacitively storing electrical energy within the enclosure of an aircraft airframe of claim 1 wherein said step of fabricating substantial portions of said airframe from structural materials comprised of intimately spaced electrically isolated and electrical capacitance-comprising first and second electrical conductors disposed in a woven fabric includes one of: sputtering, sol gel depositing, spraying, vapor depositing and extruding a metallic coating over an elongated dielectric covered electrical conductor.