The results of development and ground tests of lithium-ion battery for space application
Aerospace propulsion engineering
Аuthors1*, 1**, 2***, 1****
1. Keldysh Research Centre, 8, Onezhskaya str., Moscow, 125438, Russia
AbstractThe design of lithium-ion battery for space application is developed. The lithium-ion battery contains prismatic lithium-ion accumulators in series connected into the electric circuit with the electronics module and the device for active equalizing voltage battery charge and discharge. The full cycle of ground tests, including electrical, mechanical, climatic tests are carried out with prototypes of battery. The program and methodology of testing, including cyclic tests simulated mode in geostationary orbit (charge current: 20 A within 120 minutes; discharge current: 40 A within 60 minutes; discharge depth - 80%) are developed for carrying out electrical tests. Battery tests were carried out in both normal climatic conditions and under vacuum (3·10-6 mm Hg). The test results showed that the actual discharge capacity at the beginning of the testing was approximately 81 A-h (the nominal capacity is 50 A-h), the actual power-intensity was approximately 2300 W-h. When cyclic battery tests on the appropriate battery modes operation on geostationary and low earth orbits in normal climatic conditions were conducting the energy efficiency was approximately 0,96, the maximum surface temperature of the batteries wasn’t greater than 22 ºС while the temperature of the cooling system plate surface was about 13,5 ºС. When cycling of the battery in a vacuum were conducting the temperature increased to 32-34 ºC while discharge current was 40 A and tendency to a slight further growth with cycling continuation was observed.
Keywords:lithium-ion battery, transport properties, discharge capacity, discharge velocity, temperature regime conditions, power-intensity
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