Systems and methods for dedicating power to a radar module

• US 7,474,249 B1
• Filed: 08/12/2005
• Issued: 01/06/2009
• Est. Priority Date: 08/12/2004
• Status: Active Grant

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Inventors: Fuchs, Henry G., Harvey, Timothy W., Williams, James D.
• Primary Examiner(s): Tarcza; Thomas H
• Assistant Examiner(s): Barker; Matthew M
• Application Number:
  US11/202,946
• Time in Patent Office: 1,243 Days
• Field of Search: 342/25.R
• US Class Current: 342/25.00R
• CPC Class Codes: B64G 1/428 Power distribution and management
• CPC Class Codes: B64G 1/44 using radiation, e.g. deployable solar arrays
• CPC Class Codes: B64G 1/66 Arrangements or adaptations of apparatus or instruments, not otherwise provided for
• CPC Class Codes: G01S 7/02 of systems according to group G01S13/00
• CPC Class Codes: H02M 3/155 using semiconductor devices only

Abstract

Systems and methods presented herein are generally directed to providing power to a radio frequency module of a radar antenna. For example, a system comprises a dedicated power cell that supplies a power signal and includes a dedicated solar power module that generates electrical energy for the power signal. The system also comprises a dedicated signal conditioner coupled to the power cell and to the radio frequency module, the signal conditioner conditioning the power signal for use by the radio frequency module. The radio frequency module receives conditioned power from the signal conditioner to use in processing a radio frequency signal. The radio frequency module may be a Synthetic Aperture Radar (“SAR”) that comprises one or more radiating elements to transmit pulsed electromagnetic energy for use in radar processing. The SAR may also comprise a receiver that receives the pulsed electromagnetic energy reflected from a target.

Claims

1. A system that supplies power to a radar antenna onboard a space vehicle, said system comprising:

a plurality of antenna modules of the radar antenna onboard the space vehicle, wherein each antenna module includes;

a radio frequency module,

a dedicated power cell that supplies a power signal to the radio frequency module of the antenna module and includes a dedicated solar power module that generates electrical energy for the power signal, and

a dedicated signal conditioner coupled to the power cell and to the radio frequency module of the antenna module, the signal conditioner conditioning the power signal for use by the radio frequency module, wherein the radio frequency module receives conditioned power from the signal conditioner to use in processing a radio frequency signal, and wherein the signal conditioner includes a dedicated voltage regulator that regulates a voltage of the power signal, wherein the voltage regulator is configured with a single ended primary inductance converter topology that includes a processor and an inductor, the processor included in the voltage regulator configured to execute software instructions to detect characteristics of the power signal and transfer the detected characteristics to a central processing system of the space vehicle, and wherein the signal conditioner further includes a dedicated charge storage unit coupled to the voltage regulator to temporarily store the power signal thereby deterring voltage droop resulting from transmission of pulsed electromagnetic energy by the radio frequency module, the charge storage unit comprising an array of integrated circuit capacitors connected in parallel.

2. The system of claim 1, wherein the radio frequency module includes:

one or more radiating elements that transmit pulsed electromagnetic energy for use in radar processing; and

a receiver that receives pulsed electromagnetic energy reflected from a target.

3. The system of claim 1, wherein the receiver is a Synthetic Aperture Radar receiver.

4. The system of claim 1, wherein the power cell further includes:

a dedicated battery that supplies the power signal, wherein the battery is coupled to the signal conditioner; and

a dedicated battery charger coupled to the solar power module and to the battery to charge the battery with electrical energy generated by the solar power module.

5. The system of claim 4, wherein the battery comprises a lithium electrochemical battery.

6. The system of claim 4, wherein the battery charger includes a processor that controls charging of the battery by providing the battery a substantially constant level of electrical energy from the solar power module and by terminating charging of the battery upon detection of an over-temperature condition at the battery, wherein the processor is further configured to decouple the battery from the signal conditioner upon detection of an under-voltage condition at the battery.

7. The system of claim 1, wherein a combined capacitance of the array of integrated circuit capacitors connected in parallel is at least 8,500 microfarads.

8. The system of claim 7, wherein the signal conditioner further includes a dedicated voltage converter coupled to the voltage regulator and to the radio frequency module, wherein the voltage converter receives the power signal and generates a negative voltage power signal therefrom for supply to the radio frequency module, and wherein the voltage converter includes a processor that provides a status of the system.

9. A method of supplying power to a radar antenna that includes a plurality of radio frequency modules, the radar antenna being onboard a space vehicle, said method comprising the steps of:

associating one solar power module of a plurality of solar power modules with one radio frequency module of the radar antenna onboard the space vehicle;

receiving solar energy with the solar power module to generate electrical energy for a power signal;

controlling the power signal to charge a battery;

using the battery to supply the power signal to the associated radio frequency module;

conditioning the power signal to maintain a substantially constant voltage for the associated radio frequency module, wherein said conditioning employs a voltage regulator configured with a single ended primary inductance converter topology that includes a processor and an inductor, and wherein said conditioning includes temporarily storing at least a portion of the power signal in an array of integrated circuit capacitors connected in parallel to deter voltage droop with the associated radio frequency module;

executing software instructions on the processor to detect characteristics of the power signal and transfer the detected characteristics to a central processing system of the space vehicle; and

consuming the power signal with the associated radio frequency module to process a radar signal.

10. The method of claim 9, wherein in said step of temporarily storing, a combined capacitance of the array of integrated circuit capacitors connected in parallel is at least 8,500 microfarads.

11. The method of claim 9, wherein conditioning the power signal includes converting at least a portion of the power signal to a negative voltage power signal for supply to the associated radio frequency module.

12. The method of claim 9, wherein controlling the power signal includes:

maintaining a substantially constant current to the battery;

terminating said substantially constant current to the battery upon detection of an over-temperature condition at the battery; and

decoupling the battery from the signal conditioner upon detection of an under-voltage condition at the battery.

13. The method of claim 9, wherein the battery comprises a lithium electrochemical battery.

14. The method of claim 9, further comprising associating additional solar power modules with additional radio frequency modules of the radar antenna.

15. The method of claim 9, wherein the radar signal comprises a plurality of Synthetic Aperture Radar pulses and wherein the method further comprises processing the radar signal, wherein said processing the radar signal includes transmitting the radar signal and receiving a reflected radar signal, and combinations thereof.

16. A system that supplies power to a radar antenna onboard a space vehicle, comprising:

a plurality of radar cells of the radar antenna onboard the space vehicle, wherein each radar cell includes a radio frequency module and a solar power module;

means for dedicating the solar power module to the radio frequency module of the radar cell;

means for receiving solar energy to generate electrical energy for a power signal, the power signal being dedicated to the radio frequency module;

means for controlling the power signal to charge a battery;

means for using the battery to supply the power signal to the radio frequency module;

means for conditioning the power signal to maintain a substantially constant voltage for the radio frequency module, wherein said means for conditioning employ voltage regulation means configured with a single ended primary inductance converter topology that includes processing means and inductive means, and wherein said means for conditioning further employ means for temporarily storing at least a portion of the power signal in an array of integrated circuit capacitors connected in parallel to deter voltage droop with the associated radio frequency module;

software instructions executable by said processing means to detect characteristics of the power signal and transfer the detected characteristics to a central processing system of the space vehicle; and

means for consuming the power signal with the radio frequency module to transmit a radar signal.

17. The system of claim 16, wherein the battery comprises a lithium electrochemical battery.

18. The system of claim 16, further comprising additional means for receiving solar energy to generate electrical energy for additional power signals, each additional power signal being dedicated to one of a plurality of additional radio frequency modules of the radar antenna.