Pressure sensor assemblies and methods of detecting pressure within an engine
A pressure sensing system and method for an engine of an aircraft include a transceiver assembly coupled to a portion of the engine, and a pressure sensor assembly coupled to a fan blade of the engine. The transceiver assembly is configured to transmit a first signal at a first frequency and a second signal at a second frequency that differs from the first frequency. The pressure sensor assembly is configured to receive the first signal and the second signal and transmit a third signal at a third frequency that is a difference between the first frequency of the first signal and the second frequency of the second signal. The transceiver assembly is configured to receive the third signal at the third frequency. A pressure in relation to the engine is determined based on the third signal.
1. A pressure sensing system for an engine of an aircraft, the pressure sensing system comprising:
a transceiver assembly coupled to a portion of the engine; and
a pressure sensor assembly coupled to a fan blade of the engine,
wherein the transceiver assembly is configured to transmit a first signal at a first frequency and a second signal at a second frequency that differs from the first frequency, wherein the pressure sensor assembly is configured to receive the first signal and the second signal and transmit a third signal at a third frequency that is a difference between the first frequency of the first signal and the second frequency of the second signal, wherein the transceiver assembly is configured to receive the third signal at the third frequency, and wherein a pressure in relation to the engine is configured to be determined based on the third signal.
2. The pressure sensing system of claim 1 , wherein the transceiver assembly comprises:
a first transmit antenna array configured to transmit the first signal;
a second transmit antenna array configured to transmit the second signal; and
a receive antenna array configured to receive the third signal.
3. The pressure sensing system of claim 1 , wherein the pressure sensor assembly comprises a radio frequency identification (RFID) tag.
4. The pressure sensing system of claim 1 , wherein the pressure sensor assembly is mounted on the fan blade.
5. The pressure sensing system of claim 1 , further comprising a pressure determination control unit configured to determine the pressure by analyzing the third signal.
6. The pressure sensing system of claim 5 , wherein the transceiver assembly comprises the pressure determination control unit.
7. The pressure sensing system of claim 1 , further comprising one or more waveguides extending into a housing of the engine, wherein the first signal and the second signal are configured to be transmitted through the one or more waveguides, and wherein the third signal is configured to be received through the one or more waveguides.
8. The pressure sensing system of claim 7 , wherein the one or more waveguides comprise:
a first waveguide, wherein the first signal is configured to be transmitted through the first waveguide;
a second waveguide, wherein the second signal is configured to be transmitted through the second waveguide; and
a third waveguide, wherein the third signal is configured to be received through the third waveguide.
9. A pressure sensing method for an engine of an aircraft, the pressure sensing method comprising:
coupling a transceiver assembly to a portion of the engine;
coupling a pressure sensor assembly to a fan blade of the engine;
transmitting, from the transceiver assembly, a first signal at a first frequency and a second signal at a second frequency that differs from the first frequency;
receiving, by the pressure sensor assembly, the first signal and the second signal;
transmitting, by the pressure sensor assembly, a third signal at a third frequency that is a difference between the first frequency of the first signal and the second frequency of the second signal;
receiving, by the transceiver assembly, the third signal at the third frequency; and
determining a pressure in relation to the engine based on the third signal.
10. The pressure sensing method of claim 9 , wherein said transmitting, by the transceiver assembly, comprises:
transmitting, by a first transmit antenna array, the first signal; and
transmitting, by a second transmit antenna array, the second signal.
11. The pressure sensing method of claim 10 , wherein said receiving, by the transceiver assembly, comprises receiving, by a receive antenna array, the third signal.
12. The pressure sensing method of claim 9 , wherein said coupling the pressure sensor assembly comprises mounting the pressure sensor assembly on the fan blade.
13. The pressure sensing method of claim 9 , wherein said determining comprises determining, by a pressure determination control unit, the pressure by analyzing the third signal.
14. The pressure sensing method of claim 9 , further comprising:
extending one or more waveguides into a housing of the engine;
wherein said transmitting, from the transceiver assembly, comprises transmitting the first signal and the second signal through the one or more waveguides; and
wherein said receiving, by the transceiver assembly, comprises receiving the third signal through the one or more waveguides.
15. The pressure sensing method of claim 14 , wherein said transmitting from the transceiver assembly, comprises:
transmitting the first signal through a first waveguide; and
transmitting the second signal through a second waveguide.
16. The pressure sensing method of claim 15 , wherein said receiving, by the transceiver assembly, comprises receiving the third signal through a third waveguide.
17. An aircraft comprising:
an engine including a housing and a fan blade within the housing; and
a pressure sensing system comprising:
a transceiver assembly coupled to a portion of the engine;
a pressure sensor assembly coupled to the fan blade,
wherein the transceiver assembly is configured to transmit a first signal at a first frequency and a second signal at a second frequency that differs from the first frequency, wherein the pressure sensor assembly is configured to receive the first signal and the second signal and transmit a third signal at a third frequency that is a difference between the first frequency of the first signal and the second frequency of the second signal, wherein the transceiver assembly is configured to receive the third signal at the third frequency, and wherein a pressure in relation to the engine is configured to be determined based on the third signal;
one or more waveguides extending into the housing of the engine, wherein the first signal and the second signal are configured to be transmitted through the one or more waveguides, and wherein the third signal is configured to be received through the one or more waveguides; and
a pressure determination control unit configured to determine the pressure by analyzing the third signal.
18. The aircraft of claim 17 , wherein the transceiver assembly comprises:
a first transmit antenna array configured to transmit the first signal;
a second transmit antenna array configured to transmit the second signal; and
a receive antenna array configured to receive the third signal.
19. The aircraft of claim 17 , wherein the one or more waveguides comprise:
a first waveguide, wherein the first signal is configured to be transmitted through the first waveguide;
a second waveguide, wherein the second signal is configured to be transmitted through the second waveguide; and
a third waveguide, wherein the third signal is configured to be received through the third waveguide.
20. The aircraft of claim 17 , wherein the pressure sensor assembly comprises a radio frequency identification (RFID) tag.