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A system and method directed to using a PV array and laser beamed-power for aircraft and satellites is provided. More specifically, a system and method directed to a PV receiver that reduces power losses caused by variations in irradiance is provided. The use of a sloped array with a grooved cover g

A system and method directed to using a PV array and laser beamed-power for aircraft and satellites is provided. More specifically, a system and method directed to a PV receiver that reduces power losses caused by variations in irradiance is provided. The use of a sloped array with a grooved cover glass coated with reflective coating allows the system and method to receive the laser beamed power at an angle and reduce any losses while producing a maximum power output. In addition, the use of capacitors in parallel with the PV cells in the array reduces resistive losses caused by short-term optical fluctuations and assists in maximizing power output for the array.

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1. A photovoltaic (PV) array comprising: a plurality of photovoltaic (PV) cells, each PV cell of the plurality of PV cells being configured to receive at least one optical power beam and convert power from the at least one optical power beam to electrical power; andwherein the PV array has a surface

1. A photovoltaic (PV) array comprising: a plurality of photovoltaic (PV) cells, each PV cell of the plurality of PV cells being configured to receive at least one optical power beam and convert power from the at least one optical power beam to electrical power; andwherein the PV array has a surface geometry arrangement in which at least some of the plurality of PV cells are disposed at an angle with respect to the at least one optical power beam to substantially equalize irradiance of the plurality of PV cells received from the at least one optical power beam across the PV array;wherein the surface geometry arrangement is a sawtooth configuration having a plurality of cusps and a plurality of slopes; andwherein the plurality of slopes increase progressively in angle from an edge of the PV array to a center of the PV array; andwherein the surface geometry arrangement compensates for a beam intensity curve approximately equal to a beam intensity curve of a conical array. 2. The PV array of claim 1, wherein the surface geometry arrangement is a curved conical arrangement. 3. The PV array of claim 1, wherein the PV array is configured symmetrically about an axis of the PV array and forms a circular periphery. 4. The PV array of claim 1, wherein the PV array has a rectangular side profile. 5. The PV array of claim 1, wherein the PV array having a first axis and a second axis, the PV array being rotatable about the first axis and fixed with respect to the second axis, such that the angle of incidence on the PV array of the at least one optical power beam when the PV array is rotatably adjusted with respect to the at least one optical power beam provides a substantially uniform irradiance along a vertical portion of the PV array. 6. The PV array of claim 5, wherein the PV array is configured in an elliptical shape. 7. The PV array of claim 1, wherein the PV array comprises at least one string of electrically interconnected PV cells attached to a side of the PV array. 8. The PV array of claim 7 wherein the plurality of PV cells in the at least one string being electrically connected in series. 9. The PV array of claim 7 wherein each PV cell of the plurality of PV cells further includes a capacitor electrically connected in parallel therewith. 10. The PV array of claim 4 comprising a plurality of strings of PV cells, the plurality of strings in the PV array being electrically connected in parallel. 11. The PV array of claim 1 wherein the PV array further comprising a transparent, smooth window disposed over at least one surface of the PV array for reducing air turbulence when applied to an aircraft in flight. 12. The PV array of claim 1, wherein at least one PV cell of the plurality of PV cells having a coverglass covering the PV cell, and wherein the coverglass configured in a sawtooth profile having a plurality of ridges and a plurality of grooves. 13. The PV array of claim 12 wherein each groove of the plurality of grooves has a transparent first surface substantially perpendicular to the optical power beam. 14. The PV array of claim 13 wherein each groove of the plurality of grooves has a second surface, the second surface having a reflective coating and being substantially parallel to the optical power beam, wherein at least a portion of a beam impinging on the PV cell through the first surface is reflected at the reflective coating and directed back towards the PV cell to reduce reflective losses in the PV cell. 15. The PV array of claim 12 wherein the PV array is configured substantially circular or elliptical. 16. The PV array of claim 12 wherein the PV array having a first axis and a second axis, the PV array being rotatable about the first axis and fixed with respect to the second axis, such that the angle of incidence on the PV array of the at least one optical power beam when the PV array is rotatably adjusted with respect to the at least one optical power beam provides a substantially uniform irradiance along a vertical portion of the PV array. 17. A method of converting laser beam power to electrical energy with a photovoltaic (PV) array, the PV array comprised of a plurality of PV cells, the method comprising: providing the PV array on an airborne vehicle, the PV array having a sawtooth configuration having a plurality of cusps and a plurality of slopes wherein the plurality of slopes increase progressively in angle from an edge of the PV array to a center of the PV array, in which at least some of the plurality of PV cells are disposed at an angle with respect to the at least one optical power beam arranged to substantially equalize irradiance of the plurality of PV cells received from a laser beam across the PV array and wherein the surface geometry arrangement compensates for a beam intensity curve approximately equal to a beam intensity curve of a conical array;directing the at least one optical power beam toward the PV array;receiving the at least one optical power beam on the PV array;converting the at least one optical power beam into electrical power; andpowering the airborne vehicle with the converted electrical power;wherein the at least one optical power beam has a time-averaged intensity profile I(r) represented by the following equation: I(r)=I0exp(−r2/σ2)where: I0=intensity at the beam's centerr=distance from the beam's center σ=1/e fall-off distance. 18. The method of claim 17, wherein the PV array is formed by at least one string of PV cells electrically interconnected in series attached to a side of the PV array. 19. The method of claim 17, wherein each PV cell of the plurality of PV cells further includes a capacitor electrically connected in parallel therewith. 20. The method of claim 17, wherein the step of receiving the beam on the PV array further comprises rotating the PV array along a first axis with respect to a second axis, such that the at least one optical power beam when the PV array is rotatably adjusted with respect to the at least one optical power beam provides a substantially uniform irradiance along a vertical portion of the PV array. 21. The system of claim 1 wherein each slope in the plurality of slopes has an angle θ, measured from a plane of the array and a time-averaged intensity profile I(r), the angle θ defined by the following equation: θ=arccos(I(rmax)/I(r))where: I(rmax)=intensity at the array's edger=distance from the beam's centerI(r)=intensity at distance r from the beam's center. 22. The system of claim 1 wherein the optical power beam has a time-averaged intensity profile I(r) represented by the following equation: I(r)=I0exp(−r2/σ2)where: I0=intensity at the beam's centerr=distance from the beam's centerσ=1/e fall-off distance.