-
1.发明授权公开(公告)号：US10782191B2
公开(公告)日：2020-09-22
申请号：US15913715
申请日：2018-03-06
发明人： Mark Sherwood Miller , Robert J. Norris , Lei Liu
摘要： A system configured to monitor temperature in a plurality of zones of an aircraft includes an optical fiber with first and second ends, first and second connectors, and a first interrogator. The optical fiber includes a plurality of fiber Bragg gratings disposed in the optical fiber. The first connector is disposed on the first end of the optical fiber and the second connector is disposed on the second end of the optical fiber. The first interrogator is connected to the first connector and includes an optical switch. The optical switch is in optical communication with the first connector of the optical fiber and is configured to selectively block transmission of the optical signal to the optical fiber.
-
公开(公告)号：US10112726B2
公开(公告)日：2018-10-30
申请号：US15600077
申请日：2017-05-19
发明人： Christopher Wilson , David William Frasure , Mark Thomas Kern , Mark Sherwood Miller , Scott Kenneth Newlin , Chris George Georgoulias , Stefan Coreth , Ken Bell
IPC分类号： G01M17/00 , B64D45/00 , G08C23/04 , H04J14/08 , H04J14/02 , H04B10/071 , G07C5/08 , G01K11/32 , G02B6/42 , G02B6/34
摘要： Overheat and fire detection for aircraft systems includes an optical controller and a fiber optic loop extending from the optical controller. The fiber optic loop extends through one or more zones of the aircraft. An optical signal is transmitted through the fiber optic loop from the optical controller and is also received back at the optical controller. The optical controller analyzes the optical signal to determine the temperature, strain, or both experienced within the zones.
-
公开(公告)号：US10585006B2
公开(公告)日：2020-03-10
申请号：US15600049
申请日：2017-05-19
发明人： Christopher Wilson , David William Frasure , Mark Thomas Kern , Mark Sherwood Miller , Scott Kenneth Newlin , Chris George Georgoulias , Stefan Coreth , Ken Bell
摘要： Overheat and fire detection for aircraft systems includes an optical controller and a fiber optic loop extending from the optical controller. The fiber optic loop extends through one or more zones of the aircraft. An optical signal is transmitted through the fiber optic loop from the optical controller and is also received back at the optical controller. The optical controller analyzes the optical signal to determine the temperature, strain, or both experienced within the zones.
-
公开(公告)号：US20230092269A1
公开(公告)日：2023-03-23
申请号：US17529868
申请日：2021-11-18
IPC分类号： G01K11/3206 , G01H9/00 , B64D45/00
摘要： A detection system in an aircraft includes an optical fiber arranged along a structure of the aircraft and affixed to the structure with clamps that are spaced apart along the structure. The optical fiber includes two or more sets of fiber Bragg gratings (FBGs). The system also includes a light source to generate light with two or more wavelengths for injection into the optical fiber, and processing circuitry to identify an overheat condition and monitor vibration experienced by the optical fiber based on reflected signals generated by the two or more sets of FBGs. Integrity of the clamps is indicated by monitoring the vibration.
-
公开(公告)号：US10768055B2
公开(公告)日：2020-09-08
申请号：US15913664
申请日：2018-03-06
发明人： Mark Sherwood Miller
摘要： A system configured to monitor a plurality of zones of an aircraft includes a line replaceable unit, a first interrogator, and a controller. The line replaceable unit includes first and second connectors in optical communication and an optical fiber. The optical fibers includes a first plurality of fiber Bragg gratings and a plurality of calibration fiber Bragg gratings in a pattern providing information related to a calibration value based upon a center wavelength of each of the first plurality of fiber Bragg gratings. The first interrogator is connected to the line replaceable unit at the first end of the optical fiber and is configured to provide a first optical signal and to receive a first optical response signal from the optical fiber. The controller is operatively connected to the first interrogator and is configured to determine the calibration value of the line replaceable unit.
-
公开(公告)号：US10712212B2
公开(公告)日：2020-07-14
申请号：US16008358
申请日：2018-06-14
发明人： Lei Liu , Mark Sherwood Miller
摘要： A method for detecting and determining a location of an overheat condition includes producing a narrowband optical signal with a laser source and optical pulse generator. The optical signal is sent into the optical fiber. A plurality of reflected optical signals is received. Reflection intensities are detected using a photodetector. The reflection intensities are compared with a triggering threshold. Response times of the reflected optical signals are recorded whenever the reflection intensity of the optical signals is greater than the triggering threshold. The narrowband optical signal is adjusted to another wavelength. An anomaly reflected optical signal is identified using a characteristic of the timings obtained through a range of wavelengths. The location of the overheat condition recorded response times is calculated. The location and existence of the overheat condition is communicated.
-
公开(公告)号：US10436652B2
公开(公告)日：2019-10-08
申请号：US15600130
申请日：2017-05-19
发明人： Christopher Wilson , David William Frasure , Mark Thomas Kern , Mark Sherwood Miller , Scott Kenneth Newlin , Chris George Georgoulias , Stefan Coreth , Ken Bell
摘要： Overheat and fire detection for aircraft systems includes an optical controller and a fiber optic loop extending from the optical controller. The fiber optic loop extends through one or more zones of the aircraft. An optical signal is transmitted through the fiber optic loop from the optical controller and is also received back at the optical controller. The optical controller analyzes the optical signal to determine the temperature, strain, or both experienced within the zones.
-
公开(公告)号：US11906369B2
公开(公告)日：2024-02-20
申请号：US17529868
申请日：2021-11-18
IPC分类号： G01K11/3206 , B64D45/00 , G01K1/14 , G01H9/00
CPC分类号： G01K11/3206 , B64D45/00 , G01H9/004 , B64D2045/009 , B64D2045/0085
摘要： A detection system in an aircraft includes an optical fiber arranged along a structure of the aircraft and affixed to the structure with clamps that are spaced apart along the structure. The optical fiber includes two or more sets of fiber Bragg gratings (FBGs). The system also includes a light source to generate light with two or more wavelengths for injection into the optical fiber, and processing circuitry to identify an overheat condition and monitor vibration experienced by the optical fiber based on reflected signals generated by the two or more sets of FBGs. Integrity of the clamps is indicated by monitoring the vibration.
-
9.发明申请公开(公告)号：US20190277709A1
公开(公告)日：2019-09-12
申请号：US15913715
申请日：2018-03-06
发明人： Mark Sherwood Miller , Robert J. Norris , Lei Liu
摘要： A system configured to monitor temperature in a plurality of zones of an aircraft includes an optical fiber with first and second ends, first and second connectors, and a first interrogator. The optical fiber includes a plurality of fiber Bragg gratings disposed in the optical fiber. The first connector is disposed on the first end of the optical fiber and the second connector is disposed on the second end of the optical fiber. The first interrogator is connected to the first connector and includes an optical switch. The optical switch is in optical communication with the first connector of the optical fiber and is configured to selectively block transmission of the optical signal to the optical fiber.
-
公开(公告)号：US20190277669A1
公开(公告)日：2019-09-12
申请号：US15913696
申请日：2018-03-06
发明人： Mark Sherwood Miller
摘要： A system configured to a plurality of zones of an aircraft includes first and second connectors are in optical communication, an optical fiber, a first interrogator, and a controller. The optical fiber extends between the first and second connectors and includes a first timing fiber Bragg grating disposed in the optical fiber at a reference location of the optical fiber. The first interrogator is connected to the optical fiber and is configured to provide a first optical signal to the optical fiber and to receive a first timing signal from the optical fiber. The first timing fiber Bragg grating is configured to provide the first timing signal with information related to the first timing fiber Bragg grating from the first interrogator. The controller is operatively connected to the first interrogator and is configured to determine the reference location of the optical fiber.
-
-
-
-
-
-
-
-
-
搜索结果
16 条记录 (耗时 0.04 秒)
