Method for monitoring aircraft battery status

Claim 1

A battery condition monitoring apparatus for providing status and advice concerning a storage battery in an aircraft, comprising: (a) microprocessor means located on said aircraft for controlling the operations of said apparatus; (b) software means for instructing said microprocessor means to control the sequence of said operations; (c) memory means connected to said microprocessor means for storing said software instructions and predetermined relationships between the internal resistance of said battery, the tolerable limit of said internal resistance and the ambient temperature of said battery; (d) digital to analog converter means connected to said microprocessor means for converting digital signals from said microprocessor means to analog signals; (e) direct current power generator means, connected to said digital to analog converter means, for producing electric power at voltage and current, required by said microprocessor means; (f) current sensor means, connected to a terminal of said battery; for measuring the current passing into and out of said battery; (g) temperature sensor means, located near said battery, for measuring the ambient temperature of said battery; (h) voltmeter means for measuring the voltages of said battery, current sensor, temperature sensor and direct current power generator means; (i) analog to digital converter means, connected to said voltmeter, for converting the analog signals from the said voltage measurements to digital signals appointed for transfer to said microprocessor; (j) second software means for analyzing said current, voltages and temperature, and for determining the internal resistance and polarization of said battery, defects in said battery, and low temperature starting limit, to establish said battery maintenance and replacement requirements; (k) actuator means for controlling the electrical circuits connecting said sensors, said direct current power generating means and said battery; and (l) display means, controlled by said microprocessor for indicating said battery status and advice.

Claim 4

A method for monitoring an aircraft storage battery, which comprises the steps of: (a) measuring continuously the ambient temperature, the battery voltage, the charger output voltage, and the current to and from said battery; (b) analyzing said current-voltage (I-V) data to determine the internal resistance and polarization of said battery said, internal resistance of said battery being determined from the instantaneous change in voltage at the beginning or at the end of a current input to or output from the battery which instantaneous charge in voltage is caused by switching on or switching off charge pulse current to or discharge pulse current from said battery and said polarization of said battery being determined from a change in voltage during a predetermined time interval immediately following said instantaneous change; (c) determining the state of charge, and fault conditions, including fault conditions produced by corroded terminals, and low electrolyte level; (d) determining the low temperature limit by comparing the battery's power output capability with power requirements of said aircraft component system including the starting system; and (e) indicating data produced by said comparison.

Claim 5

A method for monitoring an aircraft storage battery, which comprises the steps of: (a) measuring continuously the ambient temperature, the battery voltage, the charger output voltage, and the current to and from said battery; (b) analyzing said current-voltage (I-V) data to determine the internal resistance and polarization of said battery said, internal resistance of said battery being determined from the instantaneous change in voltage at the beginning or at the end of a current input to or output from the battery which instantaneous charge in voltage is caused by switching on or switching off charge pulse current to or discharge pulse current from said battery and said polarization of said battery being determined from a change in voltage during a predetermined time interval immediately following said instantaneous change; (c) determining the state of charge, and fault conditions, including fault conditions produced by corroded terminals, and low electrolyte level; (d) determining the low temperature limit by comparing the battery's power output capability with power requirements of said aircraft component system including the starting system; and (e) indicating data produced by said comparison.

Claim 21

A method for monitoring an aircraft storage battery, which comprises the steps of: (a) measuring continuously the ambient temperature, the battery voltage, the charger output voltage, and the current to and from said battery; (b) analysing said current-voltage (I-V) data to determined the internal resistance and polarization of said battery, and to determine therefrom battery life and fault conditions produced from corroded terminals and low electrolyte level; (c) determining the state of charge, and fault conditions by: (i) subjecting said battery to a special test cycle wherein a predetermined profile of current or voltage having increasing applied current or voltage (ramp up) and decreasing applied current or voltage (ramp down) directions is imposed onto the battery by the charging system and the battery response voltage or current is measured, the state of charge being determined from the current at which gas inside said battery stops evolving in the ramp down direction; (ii) evaluating the data in the forms, dV/dI versus I, or dI/dV versus V; (iii) determining the battery characteristics, including the capacity, and the voltage; (iv) determining the battery defects, including mismatched cell, soft-shorted cell, and loss of capacity; and (v) indicating said data and advice; (d) determining the low temperature limit by comparing the battery's power output capability with power requirements of said aircraft component system including the starting system, the determination of engine starting power requirements being made at various temperatures by extrapolating the power actually used by the engine at any one temperature using a predetermined mathematical function or graphical data that relates the battery's power output capability with various temperatures; and (e) indicating data produced by said comparison.

Claim 22

A method for monitoring an aircraft storage battery, which comprises the steps of: (a) measuring continuously the ambient temperature, the battery voltage, the charger output voltage, and the current to and from said battery; (b) analysing said current-voltage (I-V) data to determined the internal resistance and polarization of said battery, and to determine therefrom battery life and fault conditions produced from corroded terminals and low electrolyte level; (c) determining the state of charge, and fault conditions by: (i) subjecting said battery to a special test cycle wherein a predetermined profile of current or voltage having increasing applied current or voltage (ramp up) and decreasing applied current or voltage (ramp down) directions is imposed onto the battery by the charging system and the battery response voltage or current is measured, the state of charge being determined from the current at which gas inside said battery stops evolving in the ramp down direction; (ii) evaluating the data in the forms, dV/dI versus I, or dI/dV versus V; (iii) determining the battery characteristics, including the capacity, and the voltage; (iv) determining the battery defects, including mismatched cell, soft-shorted cell, and loss of capacity; and (v) indicating said data and advice; (d) determining the low temperature limit by comparing the battery's power output capability with power requirements of said aircraft component system including the starting system, the determination of engine starting power requirements being made at various temperatures by extrapolating the power actually used by the engine at any one temperature using a predetermined mathematical function or graphical data that relates the battery's power output capability with various temperatures; and (e) indicating data produced by said comparison.

Claim 23

A method for monitoring an aircraft storage battery, which comprises the steps of: (a) measuring continuously the ambient temperature, the battery voltage, the charger output voltage, and the current to and from said battery; (b) analysing said current-voltage (I-V) data to determine the internal resistance and polarization of said battery and to determine therefrom battery life and fault conditions produced from corroded terminals and low electrolyte level; (c) determining the state of charge, and fault conditions by: (i) subjecting said battery to a special test cycle wherein a predetermined profile of current or voltage having increasing applied current or voltage (ramp up) and decreasing applied current or voltage (ramp down) directions is imposed onto the battery by the charging system and the battery response voltage or current is measured; (ii) evaluating the data in the forms, dV/dI versus I, or dI/dV versus V; (iii) determining the battery characteristics, including the capacity, and the voltage, said battery capacity being determined from the current at which said battery starts evolving gas in said battery in the ramp up direction; (iv) determining the battery defects, including mismatched cell, soft-shorted cell, and loss of capacity; and (v) indicating said data and advice; (d) determining the low temperature starting limit by comparing the battery's power output capability with starting power requirements of said aircraft component system including the starting system, the determination of engine starting power requirements being made at various temperatures by extrapolating the power actually used by the engine at any one temperature using a predetermined mathematical function or graphical data that relates the battery's power output capability with various temperatures; and (e) indicating data produced by said comparison.

Claim 24

A method for monitoring an aircraft storage battery, which comprises the steps of: (a) measuring continuously the ambient temperature, the battery voltage, the charger output voltage, and the current to and from said battery; (b) analysing said current-voltage (I-V) data to determine the internal resistance and polarization of said battery and to determine therefrom battery life and fault conditions produced from corroded terminals and low electrolyte level; (c) determining the state of charge, and fault conditions by: (i) subjecting said battery to a special test cycle wherein a predetermined profile of current or voltage having increasing applied current or voltage (ramp up) and decreasing applied current or voltage (ramp down) directions is imposed onto the battery by the charging system and the battery response voltage or current is measured; (ii) evaluating the data in the forms, dV/dI versus I, or dI/dV versus V; (iii) determining the battery characteristics, including the capacity, and the voltage, said battery capacity being determined from the current at which said battery starts evolving gas in said battery in the ramp up direction; (iv) determining the battery defects, including mismatched cell, soft-shorted cell, and loss of capacity; and (v) indicating said data and advice; (d) determining the low temperature starting limit by comparing the battery's power output capability with starting power requirements of said aircraft component system including the starting system, the determination of engine starting power requirements being made at various temperatures by extrapolating the power actually used by the engine at any one temperature using a predetermined mathematical function or graphical data that relates the battery's power output capability with various temperatures; and (e) indicating data produced by said comparison.