Super capacitor battery clone

  • US 5,850,113 A
  • Filed: 04/15/1997
  • Issued: 12/15/1998
  • Est. Priority Date: 04/15/1997
  • Status: Expired due to Fees
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First Claim
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1. Direct current aircraft electrical energy distribution apparatus comprising the combination of:

  • a source of direct current electrical energy located in a first portion of said aircraft;

    an electrical bus having electrical bus conductors, including an electrically insulated conductor, connected with said source of direct current electrical energy, extending throughout said aircraft, including remote second portions of said aircraft, and connected in energizing relationship with a plurality of electrical transient generating aircraft electrical load devices also disposed throughout said aircraft;

    a plurality of electrical energy storage devices located at selected distributed locations disposed throughout said aircraft and connected locally to said electrical bus conductors at selected distributed bus locations, said electrical energy storage devices including a capacitor element and an energy coupling electronic converter circuit of bi-directional energy flow capability communicating transient flows of electrical energy from said electrical bus conductors to said capacitor and from said capacitor to said electrical bus conductors in response to selected bus operating conditions;

    said energy coupling electronic converter circuit comprising an electrical inductance element connected with said capacitor element and in series with said flows of electrical energy to and from said capacitor, a series connected first electrical switching element connected with said electrical inductance element and generating first electrical current undulations in said inductance element during first direction energy flows therein, a shunt-connected second electrical switching element also connected with said electrical inductance element and generating second electrical current undulations in said inductance element during second direction energy flows therein, and an electrical voltage regulator controller of pulse width time parameters of said electrical inductance element first and second electrical current undulations;

    said electrical voltage regulator controller being pulse width time parameters-responsive to voltage levels appearing on said aircraft electrical bus adjacent each said electrical energy storage device;

    said electrical voltage regulator controller including a trapezoidal waveshape regulation-determining pulsed voltage reference signal having a sloped leading edge and a flat constant voltage trailing portion of amplitude equal to a nominal operating voltage level of said aircraft electrical bus.

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