Power supply circuit for an ion engine sequentially operated power inverters

• US 6,154,383 A
• Filed: 07/12/1999
• Issued: 11/28/2000
• Est. Priority Date: 07/12/1999
• Status: Expired due to Term

• Current Assignee: L-3 Communications Electron Technologies, Inc. (L3Harris Technologies, Inc.)
• Original Assignee: Hughes Electronics Corporation (AT&T, Inc.)
• Inventors: Cardwell, Gilbert I. Jr.
• Primary Examiner(s): Berhane, Adolf Deneke
• Assistant Examiner(s): Vu, Bao Q.
• Application Number:
  US09/351,572
• Time in Patent Office: 505 Days
• Field of Search: 363/70, 363/71, 363/41, 363/98, 363/132, 363/134
• US Class Current: 363/71
• CPC Class Codes: F03H 1/0018 Arrangements or adaptations of power supply systems for cosmonautic vehicles B64G1/42
• CPC Class Codes: H02M 1/0077 Plural converter units whose outputs are connected in series
• CPC Class Codes: H02M 3/33573 Full-bridge at primary side of an isolation transformer

Abstract

A power supply circuit for an ion engine suitable for a spacecraft has a voltage bus having input line and a return line. The power supply circuit includes a pulse width modulation circuit. A plurality of bridge inverter circuits is coupled to the bus and the pulse width modulation circuit. The pulse width modulation circuit generates operating signals having a variable duty cycle. Each bridge inverter has a primary winding and a secondary winding. Each secondary winding is coupled to a rectifier bridge. Each secondary winding is coupled in series with another of the plurality of rectifier bridges.

Claims

1. A power supply circuit comprising:

a voltage bus having a input line and a return line;

a pulse width modulation circuit having a plurality of independently controllable outputs for generating respective dependent entry controllable duty cycles;

a plurality of power supply modules coupled to said bus and said pulse width modulation circuit, each module coupled to a respective one of said plurality of independently controllable outputs, each module having a primary winding and a secondary winding, each secondary winding coupled to a rectifier circuit, each rectifier circuit coupled in series, each primary winding having a voltage controlled by said pulse width modulation circuit,

whereby said pulse width modulation circuit sequentially increasing a first duty cycle of a first one of said plurality of independently controllable outputs until a predetermined duty cycle is reached, thereafter increasing a second duty cycle of a second one of said plurality of independently controllable outputs until a predetermined voltage is obtained.

2. A power supply circuit as recited in claim 1 wherein each of said power supply modules comprise a bridge inverter.

3. A power supply circuit as recited in claim 1 wherein each of the plurality of power supply modules comprise a first switch and a second switch coupling said primary winding to said input line.

4. A power supply circuit as recited in claim 3 wherein said first switch and said second switch having a respective first control input and a second control input, said first control input and said second control input coupled to a square wave generator generating a first square wave signal.

5. A power supply circuit as recited in claim 4 wherein said square generator generating a second square wave signal.

6. A power supply circuit as recited in claim 5 wherein said first square wave signal and said second square wave signal are 180 degrees out of phase.

7. A power supply circuit as recited in claim 1 wherein each the plurality of power supply modules comprise a third switch and a fourth switch coupling said primary winding to said bus return, said third switch and said fourth switch having a respective third control input and a fourth control input coupled to said pulse width modulator.

8. A circuit as recited in claim 1 wherein said first duty cycle is substantially 100 percent.

9. A spacecraft comprising:

a spacecraft housing;

a voltage bus having an input line and a return line;

a power supply circuit comprising,

a pulse width modulation circuit having a plurality of independently controllable outputs;

a plurality of power supply modules coupled to said bus and said pulse width modulation circuit, each module coupled to a respective one of said plurality of independently controllable outputs, each module having a primary winding and a secondary winding, each secondary winding coupled to a rectifier circuit, each rectifier circuit coupled in series, each primary winding having a voltage controlled by said pulse width modulation circuit,

said pulse width modulation circuit sequentially increasing a first duty cycle of a first one of said plurality of independently controllable outputs until a first duty cycle is reached, thereafter increasing a second duty cycle of a second one of said plurality of independently controllable outputs until a predetermined voltage is obtained.

10. A spacecraft as recited in claim 9 wherein each of said power supply modules comprise a bridge inverter.

11. A spacecraft as recited in claim 9 wherein each the plurality of power supply modules comprise a first switch and a second switch coupling said primary winding to said input line.

12. A spacecraft as recited in claim 11 wherein said first switch and said second switch having a respective first control input and a second control input, said first control input and said second control input coupled to a square wave generator generating a first square wave signal.

13. A spacecraft as recited in claim 12 wherein said square generator generating a second square wave signal.

14. A spacecraft as recited in claim 13 wherein said first square wave signal and said second square wave signal are 180 degrees out of phase.

15. A spacecraft as recited in claim 9 wherein each the plurality of power supply modules comprise a third switch and a fourth switch coupling said primary winding to said bus return, said third switch and said fourth switch having a respective third control input and a fourth control input coupled to said pulse width modulator.

16. A spacecraft as recited in claim 9 wherein further comprising an ion engine comprising a gas source, an anode, a cathode, and a screen, wherein said power supply is coupled to said screen.

17. A spacecraft as recited in claim 16 wherein said gas source comprises a xenon gas source.

18. A spacecraft as recited in claim 9 wherein said first duty cycle is substantially 100 percent.

19. A method for controlling a power supply circuits having at least a first inverter circuit and a second inverter circuit, said method comprising the steps of:

controlling a first inverter circuit using a first output signal of a pulse width modulating circuit, said first output signal having a first duty cycle;

increasing the first duty cycle;

after the first circuit is operating at a substantially 100 percent duty cycle, controlling a second inverter circuit using a second output signal of a pulse width modulating circuit, said second output signal having a second duty cycle;

increasing the second duty cycle to attain a predetermined voltage.

20. A method as recited in claim 19 further comprising the step of rectifying the output of the first inverter circuit when the first duty cycle is less than about 100 percent.

21. A method as recited in claim 19 further comprising the step of rectifying the output of the second inverter circuit when the second duty cycle is less than about 100 percent.

22. A method as recited in claim 19 further comprising the step of coupling a first and second switch to an input line of a bus and to a primary winding of a first transformer.

23. A method as recited in claim 19 further comprising the step of alternately operating said first switch and said second switch.

24. A method as recited in claim 19 further comprising the step of coupling a third and fourth switch to a return line of a bus and to a primary winding of a first transformer.