Optically-powered sensor systems principally for deployment on-board aircraft and in which optical data is transmitted as available electrical energy permits
Described are optical sensing systems. The systems may perform reliably in explosive environments and provide eye protection should breakage of an optical fiber be detected. Sensors of the systems additionally may be self-managing, acquiring and transmitting sensed data as available electrical power permits. The systems beneficially may be used on-board aircraft.
1. An optical sensing system for an aircraft having a fuel tank, comprising:
a. a system controller;
b. a first sensor positioned within the fuel tank of the aircraft; and
c. at least one optical fiber; and
in which (i) the system controller comprises (A) means for transmitting optical energy to the first sensor via the at least one optical fiber and (B) means for receiving optical data from the first sensor via the at least one optical fiber and (ii) the first sensor comprises (A) means, positioned within the fuel tank of the aircraft, for converting received optical energy to electrical energy and (B) means, positioned within the fuel tank of the aircraft, for transmitting optical data as available electrical energy permits.
2. An optical sensing system according to claim 1 in which the system controller further comprises means for limiting optical energy transmitted to the first sensor.
3. An optical sensing system according to claim 2 in which the means for limiting optical energy transmitted to the first sensor operates as a function of whether the first sensor has transmitted optical data during a predetermined or determinable period of time.
4. An optical sensing system according to claim 2 in which (a) the means for transmitting optical energy to the first sensor comprises a light power source and (b) the means for limiting optical energy transmitted to the first sensor operates as a function of whether electrical power available to the light power source exceeds a predetermined or determinable value.
5. An optical sensing system according to claim 1 in which (a) the first sensor further comprises a controller and (b) the means for transmitting optical data comprises a digital data encoding protocol.
6. An optical sensing system according to claim 5 in which the digital data information comprises integrity check data.
7. An optical sensing system according to claim 1 in which the first sensor further comprises means for sensing a characteristic associated with the fuel tank of the aircraft.
8. An optical sensing system according to claim 1 further comprising a second sensor and the at least one optical fiber comprises first and second optical fibers, (a) the first optical fiber conveying optical energy from the system controller to the first sensor and optical data from the first sensor to the system controller and (b) the second optical fiber conveying optical energy from the system controller to the second sensor and optical data from the second sensor to the system controller.
9. An optical sensing system according to claim 1 further comprising (a) a light power source and (b) means for adjusting a power level of the light power source for improved operational efficiency.
10. An optical sensing system according to claim 1 further comprising an electronic safety barrier for restricting a level of the transmitted or received optical energy.
11. An optical sensing system for an aircraft having a fuel tank, comprising:
a. a system controller positioned at least partially outside the fuel tank of the aircraft and configured to communicate with at least one other system of an aircraft;
b. first and second sensors positioned within the fuel tank of the aircraft; and
c. first and second optical fibers positioned at least partially outside the fuel tank of the aircraft; and
in which (i) the system controller comprises (A) means for transmitting optical energy to the first sensor via only the first optical fiber and to the second sensor via only the second optical fiber, (B) means for receiving optical data from the first sensor via only the first optical fiber and from the second sensor via only the second optical fiber, and (C) means for limiting optical energy transmitted to at least one of the first and second sensors and (ii) each of the first and second sensors comprises (A) means, positioned within the fuel tank of the aircraft, for converting received optical energy to electrical energy, (B) means, positioned within the fuel tank of the aircraft, for transmitting optical data as available electrical energy permits, and (C) a controller.
12. A sensing method comprising:
a. transmitting optical energy to a sensor positioned within a fuel tank of an aircraft via an optical fiber;
b. at the sensor positioned within the fuel tank of the aircraft, converting the optical energy to electrical energy;
c. when sufficient electrical energy exists at the sensor to do so, sensing information relating to the environment of the sensor; and
d. when sufficient electrical energy exists at the sensor to do so, transmitting the sensed information from within the fuel tank of the aircraft to a system controller via the optical fiber.
13. A sensing method according to claim 12 further comprising reducing the amount of optical energy transmitted to the sensor when the optical fiber is broken.
14. A sensing method according to claim 12 further comprising reducing the amount of optical energy transmitted to the sensor to less than an amount that would ignite flammable fluid present in the environment of the sensor.
15. An optical sensing system for an aircraft having a fuel tank, comprising:
a. a system controller positioned at least partially outside the fuel tank of the aircraft;
b. a first sensor not synchronized with the system controller; and
c. at least one optical fiber; and
in which (i) the system controller comprises (A) means for transmitting optical energy to the first sensor via the at least one optical fiber and (B) means for receiving optical data from the first sensor via the at least one optical fiber and (ii) the first sensor comprises (A) means for converting received optical energy to electrical energy and (B) means for transmitting optical data as available electrical energy permits, such means comprising a microcontrol unit positioned within the fuel tank of the aircraft and configured to acquire sensed information as available electrical energy permits.
16. An optical sensing system according to claim 15 in which the system controller further comprises means for limiting optical energy transmitted to the first sensor.
17. An optical sensing system according to claim 16 in which the means for limiting optical energy transmitted to the first sensor operates as a function of whether the first sensor has transmitted optical data during a predetermined or determinable period of time.
18. An optical sensing system according to claim 16 in which (a) the means for transmitting optical energy to the first sensor comprises a light power source and (b) the means for limiting optical energy transmitted to the first sensor operates as a function of whether electrical power available to the light power source exceeds a predetermined or determinable value.
19. An optical sensing system according to claim 15 in which (a) the first sensor further comprises a controller and (b) the means for transmitting optical data comprises a digital data encoding protocol.
20. An optical sensing system according to claim 15 in which the first sensor further comprises means for sensing a characteristic associated with the fuel tank of the aircraft.
21. An optical sensing system according to claim 15 further comprising a second sensor and the at least one optical fiber comprises first and second optical fibers, (a) the first optical fiber conveying optical energy from the system controller to the first sensor and optical data from the first sensor to the system controller and (b) the second optical fiber conveying optical energy from the system controller to the second sensor and optical data from the second sensor to the system controller.