Structural Health Monitoring of Cryogenic Fuel Tanks
A method of health monitoring aircraft fuel system structures can include monitoring guided waves emitted by at least one guided wave emitter mounted to an inner hydrogen tank using at least one guided wave detector mounted to the inner hydrogen tank to monitor for a change versus a first baseline. The method can include monitoring guided waves emitted by at least one guided wave emitter mounted to an outer hydrogen tank surrounding the inner hydrogen tank using at least one guided wave detector mounted to the outer tank to monitor for a change versus a second baseline. The method includes outputting an alert to at least one of aircraft avionics and/or an onboard integrated Vehicle Health Management system (IVHM) if a change versus either or both of the first or second baselines is detected.
1 . A fuel system for an aircraft comprising:
a cryogenic storage system for hydrogen fuel including an inner tank configured for direct contact with cryogenic hydrogen therein, and an outer tank surrounding the inner tank, wherein the outer tank is spaced apart from the inner tank by an insulation gap; and
a first guided wave sensor array mounted to an outer surface of the inner tank.
2 . The system as recited in claim 1 , further comprising a second guided wave sensor array mounted to a surface of the outer tank wherein the outer tank is mounted as a load bearing structure of an aircraft.
3 . The system as recited in claim 2 , further comprising a controller operatively connected to the first guided wave sensor array and to the second guided wave sensor array to control the first and second guided wave sensor arrays for structural health monitoring of the inner and outer tanks.
4 . The system as recited in claim 3 , wherein the first guided wave sensor array includes at least one guided wave emitter, and at least one guided wave detector spaced apart from one another on the outer surface of the inner tank.
5 . The system as recited in claim 4 , wherein the controller includes logic configured to cause the controller to monitor guided waves emitted by the at least one guided wave emitter using the at least one guided wave detector to monitor for a change versus a baseline, and to output an alert if a change versus the baseline is detected.
6 . The system as recited in claim 3 , wherein the second guided wave sensor array includes at least one guided wave emitter, and at least one guided wave detector spaced apart from one another on the outer surface of the outer tank.
7 . The system as recited in claim 6 , wherein the controller includes logic configured to cause the controller to monitor guided waves emitted by the at least one guided wave emitter using the at least one guided wave detector to monitor for a change versus a baseline, and to output an alert if a change versus the baseline is detected.
8 . The system as recited in claim 1 , wherein the inner tank includes liquid hydrogen fuel connected in fluid communication to an aircraft propulsion system through a fuel port communicating through the insulation gap.
9 . The system as recited in claim 1 , wherein the inner tank includes cryo-compressed hydrogen fuel connected in fluid communication to an aircraft propulsion system through a fuel port communicating through the insulation gap.
10 . The system as recited in claim 1 , wherein the insulation gap is evacuated relative to ambient pressure.
11 . The system as recited in claim 1 , wherein the insulation gap is an insulative vacuum with respect to heat transfer between the inner tank and an ambient environment external to the outer tank.
12 . A method of health monitoring aircraft fuel system structures comprising:
monitoring guided waves emitted by at least one guided wave emitter mounted to an inner hydrogen tank using at least one guided wave detector mounted to the inner hydrogen tank to monitor for a change versus a first baseline;
monitoring guided waves emitted by at least one guided wave emitter mounted to an outer hydrogen tank surrounding the inner hydrogen tank using at least one guided wave detector mounted to the outer tank to monitor for a change versus a second baseline; and
outputting an alert to at least one of aircraft avionics and/or an onboard integrated vehicle health monitoring system (IVHM) if a change versus either or both of the first or second baselines is detected.
13 . The method as recited in claim 12 , wherein the monitoring of the inner tank is performed with liquid hydrogen and/or cryo-compressed hydrogen housed in the inner tank.
14 . The method as recited in claim 12 , wherein the inner tank includes liquid hydrogen fuel connected in fluid communication to an aircraft propulsion system through a fuel port communicating through the insulation gap, and further comprising powering the aircraft using the liquid hydrogen fuel while monitoring the inner and outer tanks.
15 . The method as recited in claim 12 , wherein monitoring the outer tank is performed while bearing aircraft loads with the outer tank as a load bearing member.
16 . A fuel system for an aircraft comprising:
a cryogenic storage system for hydrogen fuel including an inner tank configured for direct contact with cryogenic hydrogen therein, and an outer tank surrounding the inner tank, wherein the outer tank is spaced apart from the inner tank by an insulation gap; and
a guided wave sensor array mounted to a surface of the outer tank.
17 . The system as recited in claim 16 , wherein the outer tank is mounted as a load bearing structure of an aircraft.
18 . The system as recited in claim 17 , wherein the guided wave sensor array includes at least one guided wave emitter, and at least one guided wave detector spaced apart from one another on the outer surface of the outer tank.
19 . The system as recited in claim 18 , wherein the controller includes logic configured to cause the controller to monitor guided waves emitted by the at least one guided wave emitter using the at least one guided wave detector to monitor for a change versus a baseline, and to output an alert if a change versus the baseline is detected.
20 . The system as recited in claim 16 . wherein the inner tank includes liquid hydrogen fuel connected in fluid communication to an aircraft propulsion system through a fuel port communicating through the insulation gap.