Method for dynamic heat sensing in hypersonic applications

Patent metadata

Field	Value
Publication number	US-10141624-B2
Application number	US-201615176700-A
Country	US
Kind code	B2
Filing date	Jun 8, 2016
Priority date	Jun 8, 2016
Publication date	Nov 27, 2018
Grant date	Nov 27, 2018

Abstract

A heat sensing system and method for dynamic heat sensing may be implemented in a flight vehicle having a main antenna configured for sending and/or receipt of signals. The system includes an auxiliary antenna system that is arranged within a radome of the flight vehicle for detecting temperatures around the exterior surface of the radome. The auxiliary antenna is configured for receiving and measuring infrared or optical energy. Using the measured energy, the system is configured to determine whether the detected temperature exceeds a predetermined temperature and rotating the vehicle to equalize heat around the vehicle when the current temperature exceeds the predetermined temperature.

First claim

What is claimed is:

1. A heat sensing system in a flight vehicle having a radome surrounding a main antenna configured for sending and/or receipt of a signal, the sensor system comprising:
at least one auxiliary antenna associated with a region of the radome, the at least one auxiliary antenna being configured to receive infrared or optical energy to determine a measured temperature of the region based on the infrared or optical energy;
a processor operatively coupled to the auxiliary antenna and configured to identify whether the measured temperature exceeds a predetermined temperature; and
a controller operatively coupled to the at least one auxiliary antenna and the processor,
wherein the controller receives information from the processor regarding the measured temperature; and
wherein the controller is configured to rotate the flight vehicle to a different orientation when the measured temperature exceeds the predetermined temperature.

2. The heat sensing system according to claim 1 , wherein the at least one auxiliary antenna includes a plurality of single-element infrared or optical antenna structures arranged within the radome.

3. The heat sensing system according to claim 2 , wherein the at least one auxiliary antenna includes at least four single-element infrared or optical antenna structures.

4. The heat sensing system according to claim 2 , wherein the main antenna includes a plurality of radio-frequency radiating elements that correspond to the plurality of single-element infrared or optical antenna structures, each of the plurality of single-element infrared or optical antenna structures being positioned on a portion of a corresponding one of the plurality of radio-frequency radiating elements.

5. The heat sensing system according to claim 2 , wherein the radome includes a plurality of regions and each of the infrared or optical antenna structures is associated with one of the plurality of regions to detect the measured temperature of the respective region.

6. The heat sensing system according to claim 2 , wherein each of the plurality of infrared or optical antenna structures has a distinctive directivity radiation pattern.

7. The heat sensing system according to claim 6 , wherein each distinctive directivity radiation pattern is in an upward direction within the radome.

8. The heat sensing system according to claim 2 , wherein the at least one auxiliary antenna is a Yagi-Uda antenna structure.

9. The heat sensing system according to claim 1 , wherein the at least one auxiliary antenna is configured in an asymmetric spiral shape.

10. The heat sensing system according to claim 1 , wherein the at least one auxiliary antenna is configured in a microstrip dipole shape.

11. The heat sensing system according to claim 1 , wherein the at least one auxiliary antenna is configured in a square spiral shape.

12. The heat sensing system according to claim 1 , wherein the radome is formed of a dielectric material and the at least one auxiliary antenna is embedded in the dielectric material.

13. A method for dynamic heat sensing in a flight vehicle having a radome surrounding a main antenna configured for sending and/or receipt of a signal and at least one auxiliary antenna associated with a region of the radome, the method comprising:
using the at least one auxiliary antenna to receive infrared or optical energy to determine a measured temperature of the region based on the infrared or optical energy;
using a processor in communication with the auxiliary antenna to determine whether the current temperature exceeds a predetermined temperature;
sending information regarding the measured temperature from the processor to a controller that is in communication with the at least one auxiliary antenna and the processor; and
rotating the flight vehicle when the current temperature exceeds the predetermined temperature using the controller.

14. The method of claim 13 , wherein using the at least one auxiliary antenna includes using a plurality of infrared or optical antenna structures corresponding to a plurality of regions within the flight vehicle, each of the plurality of infrared or optical antenna structures positioned within one of the plurality of regions to detect the current temperature of the respective region.

15. The method of claim 14 , further including:
registering local coordinates of each of the plurality of regions;
identifying a coordinate location of each of the plurality of infrared or optical antenna structures;
correlating each of the plurality of infrared or optical antenna structures with a corresponding one of the plurality of regions;
measuring infrared or optical energy of each of the plurality of infrared or optical antenna structures;
identifying a first region of the plurality of regions that has a highest temperature of the plurality of regions;
identifying a second region of the plurality of regions that has a lowest temperature of the plurality of regions; and
determining a temperature difference between the first region and the second region.

16. The method of claim 15 , further including re-measuring the infrared or optical energy of each of the plurality of infrared or optical antenna structures when the temperature difference does not exceed a predetermined value.

17. The method of claim 16 , further including determining a coordinate difference between the first region and the second region when the temperature difference exceeds a predetermined value.

18. The method of claim 17 , wherein rotating the flight vehicle includes rotating the flight vehicle by the coordinate difference between the first region and the second region.

19. The method of claim 18 , further including continuously monitoring the current temperature of the plurality of regions of the flight vehicle after the flight vehicle has been rotated.

Assignees

• Raytheon Co

Inventors

• Stratis Glafkos K
• Vanderwyst Anton
• Sunne Wayne L
• Derrick David G

Classifications

• H01Q1/02 Primary

  Arrangements for de-icing; Arrangements for drying-out {; Arrangements for cooling; Arrangements for preventing corrosion} · CPC title

• F42B15/34

  Protection against overheating or radiation, e.g. heat shields; Additional cooling arrangements {(thermal protection fitted in or to cosmonautic vehicles B64G1/58)} · CPC title

• H01Q1/281

  Nose antennas · CPC title

• H01Q1/002

  Protection against seismic waves, thermal radiation or other disturbances, e.g. nuclear explosion; Arrangements for improving the power handling capability of an antenna · CPC title

• H01Q1/42

  Housings not intimately mechanically associated with radiating elements, e.g. radome · CPC title