Method for monitoring aircraft battery status

• US 4,968,942 A
• Filed: 02/21/1989
• Issued: 11/06/1990
• Est. Priority Date: 10/14/1988
• Status: Expired due to Term

• Current Assignee: Alliedsignal Inc.
• Original Assignee: Alliedsignal Inc.
• Inventors: Palanisamy, Thirumalai G.
• Primary Examiner(s): NOT, DEFINED
• Assistant Examiner(s): Mueller, Robert W.
• Application Number:
  US07/313,121
• Time in Patent Office: 623 Days
• Field of Search: 324/503, 324/426, 324/427, 324/430, 324/431, 324/433, 320/48, 340/636
• US Class Current: 324/430
• CPC Class Codes: G01R 31/006 on road vehicles, e.g. automobiles or trucks testing of ignition installations peculiar to internal combustion engines F02P17/00
• CPC Class Codes: G01R 31/007 using microprocessors or computers
• CPC Class Codes: G01R 31/008 on air- or spacecraft, railway rolling stock or sea-going vessels
• CPC Class Codes: G01R 31/3648 comprising digital calculation means, e.g. for performing an algorithm
• CPC Class Codes: G01R 31/374 with means for correcting the measurement for temperature or ageing
• CPC Class Codes: G01R 31/379 for lead-acid batteries
• CPC Class Codes: G01R 31/3842 combining voltage and current measurements
• CPC Class Codes: G01R 31/389 Measuring internal impedance, internal conductance or related variables
• CPC Class Codes: G01R 31/392 Determining battery ageing or deterioration, e.g. state of health

Abstract

An aircraft storage battery is monitored to determine battery capacity, state of charge and certain fault conditions. The ambient temperature, battery voltage on-board charger output voltage and current to and from the battery are continuously measured. Current voltage (I-V) data is analyzed to determine the internal resistance and polarization of the battery. A determination is made regarding state of charge and fault conditions produced by corroded terminals and low electrolyte level. The low temperature starting limit is determined by comparing the battery'"'"'s power output capability with starting power requirements of the aircraft. Data produced by the comparison are indicated on the dashboard of the vehicle.

Claims

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.

2. An apparatus according to claim 1, wherein said storage battery is a rechargeable battery including a lead acid battery and said direct current power generating means is an on-board or ground based charger means.

3. 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.

4. A method according to claim 3, further comprising the steps of:

(a) determining the aircraft component power requirements, including the engine starting power requirements at various temperatures by extrapolating the power actually used by the said component at any one temperature using a predetermined mathematical function or graphical data that relates the battery'"'"'s power output capability with various temperatures.

5. A method as in claim 4 wherein the aircraft component power requirements, including the engine power requirements are determined from the required rating of said battery, as recommended by the component manufacturer.

6. A method as recited by claim 4, wherein the internal resistance is determined from battery voltage and current data collected while switching on or switching off of a discharge pulse current from the battery, said discharge pulse being caused by a starter load or other accessory load.

7. A method as recited by claim 4, wherein the internal resistance is determined from battery voltage and current data collected while switching on or switching off of a charge pulse current to said battery from the charger.

8. A method as recited by claim 4, further comprising the step of determining battery capacity by measuring the charge input to the battery and the corresponding increase in the battery voltage.

9. A method as recited by claim 4, wherein the state of charge of said battery is determined from the open circuit voltage when there is no change in said open circuit voltage, and from counting the charge into and out of said battery starting from a predetermined charged state as determined from said open circuit voltage when said battery open circuit voltage is not substantially constant.

10. A method as recited by claim 4, wherein the internal resistance of the battery is determined by dividing the difference between the last battery voltage reading when the engine is in an off condition and the first battery voltage reading during engine starting condition by the current passing out of said battery during said starting condition.

11. A method as recited by claim 4, wherein the polarization of said battery is determined by dividing the difference between the first battery voltage reading and the battery voltage reading after a preset interval of time during engine starting condition by the current passing out of said battery during said starting condition.

12. A method as recited by claim 4, wherein a low electrolyte level and a need for addition of water are indicated when said polarization and internal resistance are larger than a predetermined levels and said state of charge and capacity are above preset levels.

13. A method as recited by claim 4, wherein corroded terminals and a need for cleaning terminals are indicated when state of charge and capacity of said battery are above preset levels, the internal resistance is higher than a preset limit and said polarization is below a preset limit.

14. A method as recited by claim 4, wherein end of useful life of said battery and a need to change it are indicated, upon detection of (i) one or more soft-shorted cells or (ii) internal resistance higher than a preset limit, together with normal polarization and state of charge higher than a preset limit.

15. A method as recited by claim 4, wherein presence of a soft shorted cell is detected by decrease of said battery'"'"'s open circuit voltage to a stable value lower than a preset level.

16. A method as recited by claim 4, further comprising the step of switching the charger on and off to keep the battery'"'"'s state of charge within a preset limit.

17. A method as recited by claim 4, further comprising the steps of:

(a) subjecting said battery to a special test cycle wherein a predetermined profile of current or voltage is imposed onto the battery by the charging system and the battery response voltage or current is measured;

(b) evaluating the data in the forms, dV/dI versus I, or dI/dV versus V;

(c) determining the battery characteristics, including the capacity, and the voltage;

(d) determining the battery defects, including mismatched cell, soft-shorter cell, and loss of capacity; and

(e) indicating said data and advice.

18. A method as recited by claim 17, wherein the end of useful life of said battery is indicated by the presence of mismatched cells or soft-shorted cells.

19. 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.

20. 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.