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Battery regulated bus spacecraft power control system

  • US 5,530,335 A
  • Filed: 05/11/1993
  • Issued: 06/25/1996
  • Est. Priority Date: 05/11/1993
  • Status: Expired due to Term
First Claim
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1. A power system for supplying electrical power over a power bus to at least one power consuming electrical device, comprising:

  • a plurality of uni-directional current conducting power sources, said power sources being connected to said power bus for supplying DC current thereto;

    each of said power sources, comprising;

    a solar panel for converting solar energy to a dc voltage and a variable transconductance means connected in electrical series circuit, said variable transconductance means having a controllable duty cycle, whereby the quantity of current that passes therethrough is a dependent function of the value of said duty cycle thereof, and control input means for setting said value of said duty cycle responsive to a control input voltage;

    rechargeable battery means connected to said power bus for normally receiving current from said power bus and, responsive to interruption of said power sources, for supplying current to said bus to power said at least one electronic device; and

    digital processor means, including stored program means, coupled to said control input means of said variable transconductance means in each of said plurality of power sources for selectively individually setting the duty cycle of each of said variable transconductance means under control of said stored program means, whereby electrical power supplied by said power sources to said power bus is individually controlled by said digital processor means.

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