Method of and circuit for Ni-Cd battery charge control

• US 4,622,509 A
• Filed: 11/09/1983
• Issued: 11/11/1986
• Est. Priority Date: 10/25/1983
• Status: Expired due to Term

• Current Assignee: Agence Spatiale Europeenne
• Original Assignee: Agence Spatiale Europeenne
• Inventors: Spruijt, H. J. N.
• Primary Examiner(s): NOT, DEFINED
• Assistant Examiner(s): NOT, DEFINED
• Application Number:
  US06/550,195
• Time in Patent Office: 1,098 Days
• Field of Search: 320/2, 320/5, 320/35, 320/36
• US Class Current: 320/130
• CPC Class Codes: G01R 31/378 specially adapted for the type of battery or accumulator
• CPC Class Codes: H01M 10/486 for measuring temperature
• CPC Class Codes: H02J 7/007194 of the battery
• CPC Class Codes: H02J 7/34 Parallel operation in networks using both storage and other dc sources, e.g. providing buffering H02J7/14 takes precedence
• CPC Class Codes: Y02E 60/10 Energy storage using batteries

Abstract

Method of and circuit for Ni-Cd battery charge control, particularly on low earth orbit spacecraft, according to which battery charge is terminated when the battery temperature starts to increase following a decrease at the end of charge. The temperature of the battery is sensed at individual cell level by means of thermistors placed preferably at the geometric center of thin metal plates between the isolated cells, these plates being fixed to a common metal base plate.

Claims

1. Method of charge control for Ni-Cd batteries, which are used in particular on a low earth orbit spacecraft, wherein said batteries are subjected to high speed charge and discharge cycles, a typical cycle lasting 1.5 hours, the individual battery cells of which are electrically isolated by means of a thermally conductive material with thin metal plates between the isolated battery cells fixed to a common metal base plate, which method comprises the steps of:

sensing battery temperature at the location of said thin metal plates by means of suitable temperature sensors, and

terminating battery charge by detecting a change of sign of the first derivative of the battery temperature thus sensed, when this temperature derivative becomes positive following its negative value during charge.

2. Method according to claim 1, wherein said temperature sensors are thermistor, preferably located at the geometrical centers of said thin metal plates, said thermistors being interconnected in a series-parallel configuration.

3. Circuit for charge control of Ni-Cd batteries used in particular on a low earth orbit spacecraft, wherein said batteries are subjected to high speed charge and discharge cycles, a typical cycle lasting 1.5 hours, said circuit allowing said batteries to be charged by solar array means during the sunlight period of said spacecraft when a switch S of this circuit is closed and said batteries having the individual battery cells electrically isolated by means of a thermally conductive material with thin metal plates between the isolated battery cells fixed to a common metal base plate, said circuit comprising end-of-charge detector means which detect a change of sign of the first derivative of the battery temperature, when this temperature derivative becomes positive following its negative value during charge, and which provide a signal to open said switch S which stays open for the remainder of the sunlight period, the battery temperature being sensed by suitable sensor means, placed at the location of said thin plates.

4. Circuit according to claim 3, wherein said solar array means are sized for generating a current slightly greater than the average charging current theoretically required.

5. Circuit according to claim 4, wherein said sensor means consist of a set of thermistors which are preferably located at the geometrical centers of said thin metal plates and which are interconnected in a series-parallel configuration.

6. Circuit according to claim 5, wherein said end-of-charge detector means comprise a first operational amplifier of appropriate gain, the positive input of which is connected to the voltage that appears across said set of thermistors, when a current of predetermined intensity is passed through it, and the negative input of which is connected to a reference voltage which is the output voltage of a second operational amplifier, the negative input of which is connected directly to its output and the positive input of which is periodically connected to the output of said first operational amplifier via a switch S₁, thus forcing said reference voltage to be identical to said voltage across the set of thermistors each time switch S₁ is closed, whereas said reference voltage remains constant, by means of an grounded capacitor which maintains constant the positive input of said second operational amplifier, during the time that said switch S₁ is open, and to be equal, during this time, to the value the voltage across the set of thermistors has when said switch S₁ is closed, the output voltage of said first amplifier increasing linearly from the voltage across the set of thermistors when the temperature decreases, namely during battery charge, whereas it decreases linearly from said voltage across the set of thermistors when the battery temperature increases, namely during battery discharge, in order that said first operational amplifier amplifies, according to its predetermined gain, the voltage difference between the voltage across the set of thermistors and the reference voltage only during the time that said switch S₁ is open.

7. Circuit according to claim 6, wherein the output voltages of said first and second operational amplifiers are compared by a logic circuit which detects the end of charge during the sunlight phase of an orbit, when the battery temperature starts to increase, for a difference between said output voltages whose modulus is equal to a prefixed minimal threshold to which corresponds a minimal positive temperature derivative level, thus switching off said switch S of the charge circuit through a relay means.