Spacecraft power system architecture to mitigate spacecraft charging effects

Claim 2

An improved power system for a spacecraft for providing negatively grounded power to at least one electrical load at improved higher ambient voltages while reducing the voltage potential between said spacecraft and space plasma, said spacecraft having a spacecraft containing means, said power system having at least one means for generating electrical energy from solar energy, said at least one means for generating electrical energy from solar energy having at least one positive generator feed terminal and at least one negative generator feed terminal, and said at least one electrical load having at least one electrical load input terminal and having at least one electrical load ground terminal, said improved power system comprising: means for connecting said at least one positive generator feed terminal to said spacecraft containing means; at least one power converter to convert energy from negatively charged input into positively charged output having at least one electronic energy storage element; said at least one power converter having a power converter negative input feed and at least one power converter positive output feed; means for connecting said at least one negative generator feed terminal to said power converter negative input feed through said spacecraft containing means and electrically insulated from said spacecraft containing means; means for connecting said at least one power converter positive output feed and said at least one electrical load input terminal; and means for connecting said at least one positive generator feed terminal and said at least one electrical load ground terminal.

Claim 3

A claim according to claim 1, said power converter being at least one buck/boost power converter.

Claim 4

A claim according to claim 2, said at least one buck/boost power converter having at least one coupled inductance means.

Claim 5

A claim according to claim 2, said buck/boost power converter having at least one pulse width modulator to regulate voltage to said at least one electrical load.

Claim 6

A claim according to claim 4, said at least one buck/boost power converter having at least one coupled inductance means.

Claim 7

A claim according to claim 4, further comprising: at least one battery management system connected to said improved power system.

Claim 8

A claim according to claim 6, further comprising: at least one load management system connected to said improved power system.

Claim 9

A claim according to claim 7, further comprising: at least one means for providing feedback from said at least one load management system to said at least one buck/boost power converter; and at least one response means for modifying electrical output from said at least one buck/boost power converter responsive to said at least one means for providing feedback from said at least one load management system.

Claim 10

An improved power system for a spacecraft for providing negatively grounded power to at least one electrical load at improved higher ambient voltages while reducing the voltage potential between said spacecraft and space plasma, said spacecraft having a spacecraft containing means, said power system having at least one means for generating electrical energy from solar energy, said at least one means for generating electrical energy from solar energy having at least one positive generator feed terminal and at least one negative generator feed terminal, and said at least one electrical load having at least one electrical load input terminal and having at least one electrical load ground terminal, said improved power system comprising: at least one power converter to convert energy from negatively charged input into positively charged output having at least one electronic energy storage element; said at least one power converter having a power converter negative input feed and at least one power converter positive output feed; means for connecting said at least one negative generator feed terminal and said power converter negative input feed through said spacecraft containing means and electrically insulated from said spacecraft containing means; at least one power system common ground terminal; means for connecting said at least one positive generator feed terminal and said at least one power system common ground terminal through said spacecraft containing means and electrically insulated from said spacecraft containing means; means for connecting said at least one power system common ground terminal and said spacecraft containing means; means for connecting said at least one power converter positive output feed and said at least one electrical load input terminal; and means for connecting said at least one electrical load ground terminal and said at least one power system common ground terminal.

Claim 11

An improved power system for a spacecraft for providing negatively grounded power to at least one electrical load at improved higher ambient voltages while reducing the voltage potential between said spacecraft and space plasma, said spacecraft having a spacecraft containing means, said power system having at least one means for generating electrical energy from solar energy, said at least one means for generating electrical energy from solar energy having at least one positive generator feed terminal and at least one negative generator feed terminal, and said at least one electrical load having at least one electrical load input terminal and having at least one electrical load ground terminal, said improved power system comprising: at least one power converter to convert energy from negatively charged input into positively charged output having at least one electronic energy storage element; said at least one power converter having a power converter negative input feed and at least one power converter positive output feed; means for connecting said at least one negative generator feed terminal and said power converter negative input feed through said spacecraft containing means and electrically insulated from said spacecraft containing means; at least one power system common ground terminal; means for connecting said at least one positive generator feed terminal and said at least one power system common ground terminal through said spacecraft containing means and electrically insulated from said spacecraft containing means; means for connecting said at least one power system common ground terminal and said spacecraft containing means; means for connecting said at least one power converter positive output feed and said at least one electrical load input terminal; and means for connecting said at least one electrical load ground terminal and said at least one power system common ground terminal.

Claim 12

A claim according to claim 9, said at least one power converter being at least one buck/boost power converter.

Claim 13

A claim according to claim 10, said at least one buck/boost power converter having at least one coupled inductance means.

Claim 14

A claim according to claim 10, said at least one buck/boost power converter having at least one pulse width-modulator to regulate voltage to said at least one electrical load.

Claim 15

A claim according to claim 12, said at least one buck/boost power converter having at least one coupled inductance means.

Claim 16

A claim according to claim 10, further comprising: at least one battery management system connected to said improved power system.

Claim 17

A claim according to claim 14, further comprising: at least one load management system connected to said improved power system.

Claim 18

A claim according to claim 15, further comprising: at least one means for providing feedback from said at least one load management system to said at least one buck/boost power converter; at least one response means for modifying electrical output from said at least one buck/boost power converter responsive to said at least one means for providing feedback from said at least one load management system.

Claim 19

An improved power system for a spacecraft for providing negatively grounded power to at least one electrical load at improved higher ambient voltages while reducing the voltage potential between said spacecraft and space plasma, said spacecraft having a spacecraft containing means, said power system having at least one means for generating electrical energy from solar energy, said at least one means for generating electrical energy from solar energy having at least one positive generator feed terminal and at least one negative generator feed terminal, and said at least one electrical load having at least one electrical load input terminal and having at least one electrical load ground terminal, said improved power system comprising: at least one buck/boost power converter to convert energy from negatively charged input into positively charged output; said at least one buck/boost power converter having a power converter negative input feed and at least one power converter positive output feed; means for connecting said at least one negative generator feed terminal to said power converter negative input feed through said spacecraft containing means and electrically insulated from said spacecraft containing means; at least one power system common ground terminal; means for connecting said at least one positive generator feed terminal to said at least one power system common ground terminal through said spacecraft containing means and electrically insulated from said spacecraft containing means; means for connecting said at least one power system common ground terminal to said spacecraft containing means; means for connecting said at least one power converter positive output feed and said at least one electrical load input terminal; and means for connecting said at least one electrical load ground terminal and said at least one power system common ground terminal.

Claim 20

An improved power system for a spacecraft for providing negatively grounded power to at least one electrical load at improved higher ambient voltages while reducing the voltage potential between said spacecraft and space plasma, said spacecraft having a spacecraft containing means, said power system having at least one means for generating electrical energy from solar energy, said at least one means for generating electrical energy from solar energy having at least one positive generator feed terminal and at least one negative generator feed terminal, and said at least one electrical load having at least one electrical load input terminal and having at least one electrical load ground terminal, said improved power system comprising: at least one buck/boost power converter to convert energy from negatively charged input into positively charged output; said at least one buck/boost power converter having a power converter negative input feed and at least one power converter positive output feed; means for connecting said at least one negative generator feed terminal to said power converter negative input feed through said spacecraft containing means and electrically insulated from said spacecraft containing means; at least one power system common ground terminal; means for connecting said at least one positive generator feed terminal to said at least one power system common ground terminal through said spacecraft containing means and electrically insulated from said spacecraft containing means; means for connecting said at least one power system common ground terminal to said spacecraft containing means; means for connecting said at least one power converter positive output feed and said at least one electrical load input terminal; and means for connecting said at least one electrical load ground terminal and said at least one power system common ground terminal.

Claim 21

A claim according to claim 17, said at least one buck/boost power converter having at least one pulse width modulator to regulate voltage to said at least one electrical load.

Claim 22

A claim according to claim 18, said at least one buck/boost power converter having at least one coupled inductance means.

Claim 23

A claim according to claim 19, further comprising: at least one battery management system connected to said improved power system.

Claim 24

A claim according to claim 20, further comprising: at least one load management system connected to said improved power system.

Claim 25

A claim according to claim 21, further comprising: at least one means for providing feedback from said at least one load management system to said power converter; and at least one response means for modifying electrical output from said at least one power converter responsive to said at least one means for providing feedback from said at least one load management system.

Claim 26

An improved power system for a spacecraft for providing negatively grounded power to at least one electrical load at improved higher ambient voltages while reducing the voltage potential between said spacecraft and space plasma, said spacecraft having a spacecraft containing means, said power system having at least one means for generating electrical energy from solar energy, said at least one means for generating electrical energy from solar energy having at least one positive generator feed terminal and at least one negative generator feed terminal, and said at least one electrical load having at least one electrical load input terminal and having at least one electrical load ground terminal, said improved power system comprising: at least one power system common ground terminal; means for connecting said at least one positive generator feed terminal to said at least one power system common ground terminal through said spacecraft containing means and electrically insulated from said spacecraft containing means; means for connecting said at least one power system common ground terminal to said spacecraft containing means; at least one buck/boost power converter to convert energy from negatively charged input into positively charged output; said at least one buck/boost power converter having at least one pulse width modulator to regulate voltage to said at least one electrical load; said at least one buck/boost power converter having a power converter negative input feed and at least one power converter positive output feed; means for connecting said at least one negative generator feed terminal to said power converter negative input feed through said spacecraft containing means and electrically insulated from said spacecraft containing means; at least one load management system; means for connecting said at least one power converter positive output feed of said at least one buck/boost power converter and said at least one load management system; means for connecting said at least one load management system and said at least one electrical load input terminal; means for connecting said at least one electrical load ground terminal and said at least one power system common ground terminal; at least one battery management system connected to said improved power system; at least one means for providing feedback from said at least one load management system to said at least one buck/boost power converter; and at least one response means for modifying electrical output from said at least one buck/boost power converter responsive to said at least one means for providing feedback from said at least one load management system; so that when said power system is operating, said spacecraft containing means cooperates with said at least one means for generating electrical energy from solar energy and said at least one buck/boost power converter to positively charge said spacecraft containing means, thereby allowing an ambient operating voltage of said power system greater than 28 V at positive ion repelling potential between said spacecraft containing means and space plasma adjacent to said spacecraft, thereby reducing sputtering and contamination of said spacecraft containing means, and reducing arcing with respect to the surface of said spacecraft containing means, and to thereby permit said at least one electrical load to be negatively grounded to said at least one positive generator feed terminal, said ambient operating voltage greater than 28 V reducing ambient amperage required for a given power demand requirement, thereby permitting a smaller cross section and mass of each said means for connecting.

Claim 27

An improved power system for a spacecraft for providing negatively grounded power to at least one electrical load at improved higher ambient voltages while reducing the voltage potential between said spacecraft and space plasma, said spacecraft having a spacecraft containing means, said power system having at least one means for generating electrical energy from solar energy, said at least one means for generating electrical energy from solar energy having at least one positive generator feed terminal and at least one negative generator feed terminal, and said at least one electrical load having at least one electrical load input terminal and having at least one electrical load ground terminal, said improved power system comprising: at least one power system common ground terminal; means for connecting said at least one positive generator feed terminal to said at least one power system common ground terminal through said spacecraft containing means and electrically insulated from said spacecraft containing means; means for connecting said at least one power system common ground terminal to said spacecraft containing means; at least one buck/boost power converter to convert energy from negatively charged input into positively charged output; said at least one buck/boost power converter having at least one pulse width modulator to regulate voltage to said at least one electrical load; said at least one buck/boost power converter having a power converter negative input feed and at least one power converter positive output feed; means for connecting said at least one negative generator feed terminal to said power converter negative input feed through said spacecraft containing means and electrically insulated from said spacecraft containing means; at least one load management system; means for connecting said at least one power converter positive output feed of said at least one buck/boost power converter and said at least one load management system; means for connecting said at least one load management system and said at least one electrical load input terminal; means for connecting said at least one electrical load ground terminal and said at least one power system common ground terminal; at least one battery management system connected to said improved power system; at least one means for providing feedback from said at least one load management system to said at least one buck/boost power converter; and at least one response means for modifying electrical output from said at least one buck/boost power converter responsive to said at least one means for providing feedback from said at least one load management system; so that when said power system is operating, said spacecraft containing means cooperates with said at least one means for generating electrical energy from solar energy and said at least one buck/boost power converter to positively charge said spacecraft containing means, thereby allowing an ambient operating voltage of said power system greater than 28 V at positive ion repelling potential between said spacecraft containing means and space plasma adjacent to said spacecraft, thereby reducing sputtering and contamination of said spacecraft containing means, and reducing arcing with respect to the surface of said spacecraft containing means, and to thereby permit said at least one electrical load to be negatively grounded to said at least one positive generator feed terminal, said ambient operating voltage greater than 28 V reducing ambient amperage required for a given power demand requirement, thereby permitting a smaller cross section and mass of each said means for connecting.

Claim 28

A claim according to claim 23, said at least one buck/boost power converter having at least one coupled inductance means.

Claim 29

An improved method of supplying power for a spacecraft power system for a spacecraft transporting at least one electrical load at improved higher ambient voltages while reducing the voltage potential between said spacecraft and space plasma, said spacecraft having a spacecraft containing means, said spacecraft having at least one means for generating electrical energy from solar energy, said at least one means for generating electrical energy from solar energy having at least one positive power feed terminal and at least one negative power feed terminal, and said at least one electrical load having at least one electrical load input terminal and having at least one electrical load ground terminal, said improved method comprising: connecting said at least one positive power feed terminal and said spacecraft containing means; converting energy from a negative input to a positive output using at least one power converter having at least one electronic energy storage element, said at least one power converter having a power converter negative input feed and at least one power converter positive output feed; connecting said at least one negative power feed terminal to said power converter negative input feed through said spacecraft containing means and electrically insulated from said containing means; connecting said at least one power converter positive output feed and said at least one electrical load input terminal; and connecting said at least one electrical load ground terminal and said at least one positive power feed terminal.

Claim 30

An improved method of supplying power for a spacecraft power system for a spacecraft transporting at least one electrical load at improved higher ambient voltages while reducing the voltage potential between said spacecraft and space plasma, said spacecraft having a spacecraft containing means, said spacecraft having at least one means for generating electrical energy from solar energy, said at least one means for generating electrical energy from solar energy having at least one positive power feed terminal and at least one negative power feed terminal, and said at least one electrical load having at least one electrical load input terminal and having at least one electrical load ground terminal, said improved method comprising: connecting said at least one positive power feed terminal and said spacecraft containing means; converting energy from a negative input to a positive output using at least one power converter having at least one electronic energy storage element, said at least one power converter having a power converter negative input feed and at least one power converter positive output feed; connecting said at least one negative power feed terminal to said power converter negative input feed through said spacecraft containing means and electrically insulated from said containing means; connecting said at least one power converter positive output feed and said at least one electrical load input terminal; and connecting said at least one electrical load ground terminal and said at least one positive power feed terminal.

Claim 31

A method according to claim 25, further comprising: said at least one power converter being at least one buck/boost power converter.

Claim 32

A method according to claim 26, further comprising: regulating voltage to said at least one electrical load by means of at least one pulse width modulator.

Claim 33

A method according to claim 27, further comprising: connecting at least one battery management system and said spacecraft power system.

Claim 34

A method according to claim 28, said method further comprising: connecting at least one load management system and said spacecraft power system.

Claim 35

A method according to claim 29, further comprising: connecting at least one means for providing feedback from said at least one load management system; and modifying electrical output from said at least one buck/boost power converter responsive to said at least one means for providing feedback.

Claim 36

A method according to claim 30, further comprising: said at least one buck/boost power converter having at least one coupled inductance means.

Claim 37

An improved method of supplying power for a spacecraft power system for a spacecraft transporting at least one electrical load at improved higher ambient voltages while reducing the voltage potential between said spacecraft and space plasma, said spacecraft having a spacecraft containing means, said spacecraft having at least one means for generating electrical energy from solar energy, said at least one means for generating electrical energy from solar energy having at least one positive power feed terminal and at least one negative power feed terminal, and said at least one electrical load having at least one electrical load input terminal and having at least one electrical load ground terminal, said improved method comprising: converting energy from a negative input to a positive output using at least one power converter having at least one electronic energy storage element, said at least one power converter having a power converter negative input feed and at least one power converter positive output feed; connecting said at least one negative power feed terminal to said power converter negative input feed through said spacecraft containing means and electrically insulated from said spacecraft containing means; connecting said at least one positive power feed terminal to at least one power system common ground terminal through said spacecraft containing means and electrically insulated from said spacecraft containing means; connecting said at least one power system common ground terminal to said spacecraft containing means; connecting said at least one power converter positive output feed and said at least one electrical load input terminal; and connecting said at least one electrical load ground terminal to said at least one power system common ground terminal.

Claim 38

An improved method of supplying power for a spacecraft power system for a spacecraft transporting at least one electrical load at improved higher ambient voltages while reducing the voltage potential between said spacecraft and space plasma, said spacecraft having a spacecraft containing means, said spacecraft having at least one means for generating electrical energy from solar energy, said at least one means for generating electrical energy from solar energy having at least one positive power feed terminal and at least one negative power feed terminal, and said at least one electrical load having at least one electrical load input terminal and having at least one electrical load ground terminal, said improved method comprising: converting energy from a negative input to a positive output using at least one power converter having at least one electronic energy storage element, said at least one power converter having a power converter negative input feed and at least one power converter positive output feed; connecting said at least one negative power feed terminal to said power converter negative input feed through said spacecraft containing means and electrically insulated from said spacecraft containing means; connecting said at least one positive power feed terminal to at least one power system common ground terminal through said spacecraft containing means and electrically insulated from said spacecraft containing means; connecting said at least one power system common ground terminal to said spacecraft containing means; connecting said at least one power converter positive output feed and said at least one electrical load input terminal; and connecting said at least one electrical load ground terminal to said at least one power system common ground terminal.

Claim 39

A method according to claim 32, further comprising: said at least one power converter being at least one buck/boost power converter.

Claim 40

A method according to claim 33, further comprising: regulating voltage to said at least one electrical load by means of a pulse width modulator.

Claim 41

A method according to claim 34, further comprising: connecting at least one battery management system and said spacecraft power system.

Claim 42

A method according to claim 35, said method further comprising: connecting at least one load management system and said spacecraft power system.

Claim 43

A method according to claim 36, further comprising: connecting at least one means for providing feedback from said at least one load management system; and modifying electrical output from said at least one buck/boost power converter responsive to said at least one means for providing feedback.

Claim 44

A method according to claim 37, further comprising: said at least one buck/boost power converter having at least one coupled inductance means.

Claim 45

An improved method of supplying power for a spacecraft power system for a spacecraft transporting at least one electrical load at improved higher ambient voltages while reducing the voltage potential between said spacecraft and space plasma, said spacecraft having a spacecraft containing means, said spacecraft having at least one means for generating electrical energy from solar energy, said at least one means for generating electrical energy from solar energy having at least one positive power feed terminal and at least one negative power feed terminal, and said at least one electrical load having at least one electrical load input terminal and having at least one electrical load ground terminal, said improved method comprising: converting energy from a negative input to a positive output using at least one buck/boost power converter, said at least one buck/boost power converter having a power converter negative input feed and at least one power converter positive output feed; connecting said at least one negative power feed terminal to said power converter negative input feed through said spacecraft containing means and electrically insulated from said containing means; connecting said at least one positive power feed terminal to at least one power system common ground terminal through said spacecraft containing means and electrically insulated from said containing means; connecting said at least one power system common ground terminal to said spacecraft containing means; connecting said at least one power converter positive output feed and said at least one electrical load input terminal; and connecting said at least one electrical load ground terminal to said at least one power system common ground terminal.

Claim 46

An improved method of supplying power for a spacecraft power system for a spacecraft transporting at least one electrical load at improved higher ambient voltages while reducing the voltage potential between said spacecraft and space plasma, said spacecraft having a spacecraft containing means, said spacecraft having at least one means for generating electrical energy from solar energy, said at least one means for generating electrical energy from solar energy having at least one positive power feed terminal and at least one negative power feed terminal, and said at least one electrical load having at least one electrical load input terminal and having at least one electrical load ground terminal, said improved method comprising: converting energy from a negative input to a positive output using at least one buck/boost power converter, said at least one buck/boost power converter having a power converter negative input feed and at least one power converter positive output feed; connecting said at least one negative power feed terminal to said power converter negative input feed through said spacecraft containing means and electrically insulated from said containing means; connecting said at least one positive power feed terminal to at least one power system common ground terminal through said spacecraft containing means and electrically insulated from said containing means; connecting said at least one power system common ground terminal to said spacecraft containing means; connecting said at least one power converter positive output feed and said at least one electrical load input terminal; and connecting said at least one electrical load ground terminal to said at least one power system common ground terminal.

Claim 47

A method according to claim 39, further comprising: regulating voltage to said at least one electrical load by means of a pulse width modulator.

Claim 48

A method according to claim 40, further comprising: connecting at least one battery management system and said spacecraft power system.

Claim 49

A method according to claim 41, said method further comprising: connecting at least one load management system and said spacecraft power system.

Claim 50

A method according to claim 42, further comprising: connecting at least one means for providing feedback from said at least one load management system; modifying electrical output from said at least one buck/boost power converter responsive to said at least one means for providing feedback.

Claim 51

A method according to claim 43, further comprising: said at least one buck/boost power converter having at least one coupled inductance means.

Claim 52

An improved method of supplying power for a spacecraft power system for a spacecraft transporting at least one electrical load at improved higher ambient voltages while reducing the voltage potential between said spacecraft and space plasma, said spacecraft having a spacecraft containing means, said spacecraft having at least one means for generating electrical energy from solar energy, said at least one means for generating electrical energy from solar energy having at least one positive power feed terminal and at least one negative power feed terminal, and said at least one electrical load having at least one electrical load input terminal and having at least one electrical load ground terminal, said improved method comprising: converting energy from a negative input to a positive output using at least one buck/boost power converter, said at least one buck/boost power converter having a power converter negative input feed and at least one power converter positive output feed; connecting said at least one negative power feed terminal to said power converter negative input feed through said spacecraft containing means and electrically insulated from said spacecraft containing means; connecting said at least one positive power feed terminal to at least one power system common ground terminal through said spacecraft containing means and electrically insulated from said spacecraft containing means; connecting said at least one power system common ground terminal to said spacecraft containing means; connecting said at least one power converter positive output feed to at least one load management system; connecting said at least one load management system and said at least one electrical load input terminal; connecting said at least one electrical load ground terminal and said at least one power system common ground terminal; connecting at least one means for providing feedback from said at least one load management system; modifying electrical output from said at least one buck/boost power converter responsive to said at least one means for providing feedback; regulating voltage to said at least one electrical load by means of a pulse width modulator; connecting at least one battery management system to said at least one spacecraft power system so that said containing means of said spacecraft is positively charged by said positive power feed terminal from said at least one means for generating electrical energy, thereby allowing a greater ambient operating voltage at positive ion repelling potential between said containing means and space plasma adjacent to said spacecraft, thereby reducing sputtering and contamination of said exterior surface of said spacecraft, and reducing arcing with respect to said exterior surface, thereby permitting said at least one electrical load to be negatively grounded to said at least one positive power feed terminal, and thereby reducing the ambient amperage required for a given power demand requirement.

Claim 53

An improved method of supplying power for a spacecraft power system for a spacecraft transporting at least one electrical load at improved higher ambient voltages while reducing the voltage potential between said spacecraft and space plasma, said spacecraft having a spacecraft containing means, said spacecraft having at least one means for generating electrical energy from solar energy, said at least one means for generating electrical energy from solar energy having at least one positive power feed terminal and at least one negative power feed terminal, and said at least one electrical load having at least one electrical load input terminal and having at least one electrical load ground terminal, said improved method comprising: converting energy from a negative input to a positive output using at least one buck/boost power converter, said at least one buck/boost power converter having a power converter negative input feed and at least one power converter positive output feed; connecting said at least one negative power feed terminal to said power converter negative input feed through said spacecraft containing means and electrically insulated from said spacecraft containing means; connecting said at least one positive power feed terminal to at least one power system common ground terminal through said spacecraft containing means and electrically insulated from said spacecraft containing means; connecting said at least one power system common ground terminal to said spacecraft containing means; connecting said at least one power converter positive output feed to at least one load management system; connecting said at least one load management system and said at least one electrical load input terminal; connecting said at least one electrical load ground terminal and said at least one power system common ground terminal; connecting at least one means for providing feedback from said at least one load management system; modifying electrical output from said at least one buck/boost power converter responsive to said at least one means for providing feedback; regulating voltage to said at least one electrical load by means of a pulse width modulator; connecting at least one battery management system to said at least one spacecraft power system so that said containing means of said spacecraft is positively charged by said positive power feed terminal from said at least one means for generating electrical energy, thereby allowing a greater ambient operating voltage at positive ion repelling potential between said containing means and space plasma adjacent to said spacecraft, thereby reducing sputtering and contamination of said exterior surface of said spacecraft, and reducing arcing with respect to said exterior surface, thereby permitting said at least one electrical load to be negatively grounded to said at least one positive power feed terminal, and thereby reducing the ambient amperage required for a given power demand requirement.

Claim 54

A method according to claim 45, further comprising: said at least one buck/boost power converter having at least one coupled inductance means.