Bidirectional control system for energy flow in solar powered flywheel

• US 4,649,287 A
• Filed: 07/31/1984
• Issued: 03/10/1987
• Est. Priority Date: 07/31/1984
• Status: Expired due to Fees

• Current Assignee: United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration
• Original Assignee: United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration
• Inventors: Nola, Frank J.
• Primary Examiner(s): Shoop, Jr., William M.
• Assistant Examiner(s): Ip, Shik Luen Paul
• Application Number:
  US06/636,459
• Time in Patent Office: 952 Days
• Field of Search: 307/131, 307/64, 307/80, 307/87, 307/31, 307/66, 318/161, 318/376, 318/327, 318/145, 318/146, 318/147, 318/150, 318/152, 318/107, 136/291, 136/292, 136/293, 320/39, 320/5, 244/53 R, 244/58, 244/173, 323/284, 323/283, 323/285, 323/351, 323/906, 290/1 A, 315/303, 315/306, 315/307, 315/311, 315/360
• US Class Current: 307/31
• CPC Class Codes: H02J 15/007 involving storage in the form of mechanical energy, e.g. fly-wheels
• CPC Class Codes: H02J 7/35 with light sensitive cells
• CPC Class Codes: H02M 3/158 including plural semiconductor devices as final control devices for a single load
• CPC Class Codes: Y02E 60/16 Mechanical energy storage, e.g. flywheels or pressurised fluids
• CPC Class Codes: Y02E 70/30 Systems combining energy storage with energy generation of non-fossil origin
• CPC Class Codes: Y10S 136/293 Circuits

Abstract

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.

Claims

1. 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.

2. An energy supply system as claimed in claim 1 further comprising speed sensing means for sensing the output speed of said motor and for feeding back a signal in accordance with the sensed output speed to the electrical control means so as to maintain the said output speed at a fixed maximum when an excess of solar energy is available.

3. An energy supply system as claimed in claim 1 wherein said control means includes pulse width modulation means for supplying control pulses to said electric motor.

4. An energy supply system for a spacecraft for supplying electrical energy to at least one spacecraft load, said system comprising:

a flywheel;

an electric motor-generator, connected to the flywheel for, during a first mode of operation as generator, selectively supplying electrical power to the spacecraft load and for, during a second mode of operation as a motor, selectively providing acceleration of said flywheel;

solar energy conversion means for receiving solar energy and for converting the solar energy received thereby into a corresponding output voltage; and

electrical control means including threshold comparator means for sensing the output voltage produced by said solar energy conversion means and for producing a first output when said output voltage exceeds a predetermined threshold and for producing a second output when said output voltage is less than said predetermined threshold, and a control circuit, responsive to the output said threshold comparator means, for, during an energy storage mode of operation, providing current flow from the solar energy conversion means to said spacecraft load and to said motor to accelerate said flywheel when said predetermined threshold is exceeded, and for, during a regenerative mode of operation, providing for operation of said motor as a generator so that current flows from the motor to spacecraft load;

said electrical control means further comprising speed control feedback means for sensing the speed of rotation of the flywheel and for controlling the current flow to the motor such that a constant speed of rotation of said flywheel is maintained, and further feedback means for sensing the voltage associated with the spacecraft load and for regulating the voltage supplied to the spacecraft load accordingly.

5. A system as claimed in claim 4 wherein said control circuit includes a first operational amplifier having a first input for receiving a voltage which is a function of the output of said threshold comparator means and a second input for receiving a voltage which is a function of the motor voltage, and a second operational amplifier, having a first input connected to the output of the first operational amplifier and a second input which receives a periodic ramp voltage, for producing a pulse width modulated output for controlling the operation of said motor.

6. A system as claimed in claim 5 wherein said means for sensing the voltage associated with the spacecraft load includes a further operational amplifier having one input connected to receive said associated voltage and an output connected to the said one input of said first operational amplifier so that the width of the pulses of the pulse width modulated output of the second operational amplifier are controlled accordingly.