Automated fire and smoke detection, isolation, and recovery
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0754262
(2010-04-05)
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등록번호 |
US-8322658
(2012-12-04)
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발명자
/ 주소 |
- Gershzohn, Gary R.
- Finton, David J.
- Kipersztok, Oscar
- Margineantu, Dragos D.
|
출원인 / 주소 |
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대리인 / 주소 |
Hope Baldauff Hartman, LLC
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인용정보 |
피인용 횟수 :
6 인용 특허 :
2 |
초록
▼
Technologies are described herein for detecting and recovering from a fire event within an aircraft. The technologies receive sensor data from a number of sensors associated with an aircraft. A determination is made as to whether the sensor data exceeds predefined thresholds indicating the fire even
Technologies are described herein for detecting and recovering from a fire event within an aircraft. The technologies receive sensor data from a number of sensors associated with an aircraft. A determination is made as to whether the sensor data exceeds predefined thresholds indicating the fire event within the aircraft. In response to determining that the sensor data exceeds the predefined thresholds indicating the fire event, the technologies determine a location of the fire event within the aircraft based on the sensor data and depower components of the aircraft associated with the fire event. The technologies then initiate a fire suppressant mechanism within the aircraft directed to the location of the fire event.
대표청구항
▼
1. A method for detecting and recovering from a fire event within an aircraft, the method comprising: receiving sensor data associated with fire or smoke from a plurality of sensors associated with the aircraft;determining whether the sensor data exceeds predefined thresholds indicating the fire eve
1. A method for detecting and recovering from a fire event within an aircraft, the method comprising: receiving sensor data associated with fire or smoke from a plurality of sensors associated with the aircraft;determining whether the sensor data exceeds predefined thresholds indicating the fire event within the aircraft;in response to determining that the sensor data exceeds the predefined thresholds indicating the fire event, determining a location of the fire event within the aircraft based on the sensor data;isolating and depowering electrical components of the aircraft associated with the fire event; andinitiating a fire suppressant mechanism within the aircraft directed to the location of the fire event. 2. The method of claim 1, wherein receiving sensor data from a plurality of sensors associated with an aircraft comprises at least one of receiving electrical data from electrical sensors, receiving temperature data from heat sensors, receiving chemical data from chemical sensors, receiving smoke data from smoke sensors, and receiving visual data from visual imagers. 3. The method of claim 1, wherein determining a location of the fire event within the aircraft based on the sensor data comprises determining the location of the fire event within the aircraft based on triangulation of the plurality of sensors gathering the sensor data. 4. The method of claim 1, further comprising: in response to determining that the sensor data exceeds the predefined thresholds indicating the fire event, initiating a fire containment mechanism that prevents the fire event from spreading beyond a designated area. 5. The method of claim 4, wherein initiating a fire containment mechanism that prevents the fire event from spreading beyond a designated area comprises changing airflow within the aircraft to direct the fire event away from people or dangerous goods. 6. The method of claim 1, wherein depowering components of the aircraft associated with the fire event comprises: isolating electrical components of the aircraft causing the fire event; anddepowering the electrical components of the aircraft causing the fire event. 7. The method of claim 1, wherein isolating and depowering components of the aircraft associated with the fire event comprises: isolating electrical components of the aircraft damaged by the fire event;determining whether the electrical components are critical to safe operation of the aircraft. 8. The method of claim 7, further comprising: in response to determining that the electrical components are critical to safe operation of the aircraft, requesting permission from flight crew to depower the electrical components; andupon receiving the permission from the flight crew to depower the electrical components, depowering the electrical components damaged by the fire event. 9. The method of claim 7, wherein determining whether the electrical components are critical to safe operation of the aircraft comprises determining whether the electrical components are critical to safe operation of the aircraft based on aircraft status, surrounding weather, phase of flight, and knowledge of aircraft future position. 10. The method of claim 1, wherein the fire suppressant mechanism, upon initiation, releases a fire suppressing agent directed to the location of the fire event. 11. The method of claim 1, further comprising: verifying initiation of the fire suppressant mechanism based on updated sensor data from the plurality of sensors. 12. An aircraft fire detection and recovery system, comprising: a plurality of sensors associated with an aircraft;a fire suppressant mechanism adapted to release a fire suppressing agent, the fire suppressant mechanism coupled to the aircraft;a detection module receiving sensor data associated with fire or smoke from the plurality of sensors and identifying a fire event within the aircraft when the sensor data exceeds predefined thresholds indicating the fire event within the aircraft;a localization module receiving the sensor data from the plurality of sensors and determining a location of the fire event within the aircraft based on the sensor data;an electrical component isolation module depowering electrical components of the aircraft associated with the fire event and initiating a fire containment mechanism that prevents the fire event from spreading beyond a designated area; anda decision support module initiating the fire suppressant mechanism to release the fire suppressing agent to the location of the fire event. 13. The system of claim 12, wherein the plurality of sensors comprise electrical sensors adapted to detect shorts and arc faults in an electrical system of the aircraft. 14. The system of claim 13, wherein the plurality of sensors further comprise heat sensors adapted to continuously measure temperature within the aircraft and detect sudden increases in temperature indicating the fire event. 15. The system of claim 14, wherein the plurality of sensors further comprise chemical sensors adapted to detect atmospheric constituents from the fire event that are released after the fire event has started and atmospheric constituents from chemicals that are leaked before the fire event has started. 16. The system of claim 15, wherein the plurality of sensors further comprise visual imagers adapted to capture video of visible and non-visible areas of the aircraft and smoke detectors adapted to detect smoke in the aircraft. 17. The system of claim 12, wherein the fire suppressant mechanism is electrically activated by the decision support module. 18. The system of claim 12, wherein the fire suppressant mechanism is non-electrically activated. 19. The system of claim 18, wherein the fire suppressant mechanism comprises a plurality of tubes containing a fire suppressing agent, the plurality of tubes releasing the fire suppressing agent when temperature of the fire event melts the plurality of tubes. 20. An aircraft comprising: a plurality of a sensors coupled to the aircraft, the plurality of sensors comprising (a) electrical sensors adapted to detect shorts and arc faults in an electrical system of the aircraft, (b) heat sensors adapted to continuously measure temperature within the aircraft and detect sudden increases in temperature indicating a fire event in the aircraft, (c) chemical sensors adapted to detect atmospheric constituents from the fire event that are released after the fire event has started and atmospheric constituents from chemicals that are leaked before the fire event has started, (d) visual imagers adapted to capture video of visible and non-visible areas of the aircraft, and (e) smoke detectors adapted to detect smoke in the aircraft;a fire suppressant mechanism adapted to release a fire suppressing agent, the fire suppressant mechanism coupled to the aircraft;a detection module receiving sensor data associated with fire or smoke from the plurality of sensors and identifying the fire event within the aircraft when the sensor data exceeds predefined thresholds indicating the fire event within the aircraft;a localization module receiving the sensor data from the plurality of sensors and determining a location of the fire event within the aircraft based on the sensor data;an electrical component isolation module depowering electrical components of the aircraft causing the fire event, depowering electrical components of the aircraft damaged by the fire event, and initiating the fire containment mechanism that prevents the fire event from spreading beyond a designated area; and a decision support module initiating the fire suppressant mechanism to release the fire suppressing agent to the location of the fire event.
이 특허에 인용된 특허 (2)
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Zansky,Zoltan; Tupy,Joseph, Fire protection for electronics equipment.
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Bobenhausen,Axel, Method and apparatus for fighting a fire in an enclosed space in an aircraft.
이 특허를 인용한 특허 (6)
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Ransom, John H., Suppressing a fire condition in a cargo container.
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Stehman, Keith M.; Ransom, Jr., John H., Suppressing a fire condition in an aircraft.
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Ransom, Jr., John H., Suppressing a fire condition within a cargo container.
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Stehman, Keith M.; Fisher, Richard S., System and method of notification of an aircraft cargo fire within a container.
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Stehman, Keith M.; Fisher, Richard S., System and method of notification of an aircraft cargo fire within a container.
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Koehn, Jason Andrew; Whitley, James K.; Snell, Shawn Paul, Velocity profile mapping system.
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