초록 ▼

An energy storage system for a spacecraft is provided which employs a solar powered flywheel arrangement including a motor-generator which, in different operating modes, drives the flywheel and is driven thereby. A control circuit, including a threshold comparator, senses the output of a solar energ

An energy storage system for a spacecraft is provided which employs a solar powered flywheel arrangement including a motor-generator which, in different operating modes, drives the flywheel and is driven thereby. A control circuit, including a threshold comparator, senses the output of a solar energy converter, and when a threshold voltage is exceeded thereby indicating the availability of solar power for the spacecraft loads, activates a speed control loop including the motor-generator so as to accelerate the flywheel to a constant speed and thereby store mechanical energy, while also supplying energy from the solar converter to the loads. Under circumstances where solar energy is not available and thus the threshold voltage is not exceeded, the control circuit deactivates the speed control loop and activates a voltage control loop that provides for operation of the motor as a generator so that mechanical energy from the flywheel is converted into electrical energy for supply to the spacecraft loads.

대표청구항 ▼

An energy supply system for a spacecraft for supplying energy to at least one spacecraft load, said system comprising: a flywheel; an electric motor connected to said flywheel for selectively supplying electrical power to the spacecraft load; solar energy conversion means for receiving solar energy

An energy supply system for a spacecraft for supplying energy to at least one spacecraft load, said system comprising: a flywheel; an electric motor connected to said flywheel for selectively supplying electrical power to the spacecraft load; solar energy conversion means for receiving solar energy and for converting the received solar energy into an output voltage for supply to the spacecraft load; and electrical control means for (1) sensing the spacecraft load voltage, and feeding back the sensed voltage to regulate the voltage supplied to the spacecraft load when the spacecraft load voltage changes, and for (2) comparing the output voltage from said solar energy conversion means with a threshold voltage and, when said threshold voltage is exceeded, activating a speed control loop including said motor so as to accelerate the flywheel to a constant speed to thereby convert the electrical energy supplied from said solar energy conversion means into mechanical energy, and, when said threshold voltage is not exceeded, deactivating said speed control loop and activating a voltage control loop for controlling the amount of mechanical energy from said flywheel which is converted into an electrical energy output from said motor for supply to the spacecraft load in according with the sensed load voltage.