Systems, methods, and apparatuses for taking pressure measurements are provided. A multi-hole pressure sensor probe can include a probe tip having a plurality of probe tip holes. The probe tip holes can lead to probe tip channels that convey fluid from the measurement environment to pressure transducers. The pressure transducers can operate using optical transduction techniques. A light source can be applied to the diaphragm, and the light reflected from the diaphragm changes as the position of the diaphragm changes. Further, a reflective material can be applied on the backside of the diaphragm to increase its reflective properties. The light can then be collected and analyzed using a photodiode to determine the environmental pressure acting on the different holes of the probe.

Systems, methods, and apparatuses for taking pressure measurements are provided. A multi-hole pressure sensor probe can include a probe tip having a plurality of probe tip holes. The probe tip holes can lead to probe tip channels that convey fluid from the measurement environment to pressure transducers. The pressure transducers can operate using optical transduction techniques. A light source can be applied to the diaphragm, and the light reflected from the diaphragm changes as the position of the diaphragm changes. Further, a reflective material can be applied on the backside of the diaphragm to increase its reflective properties. The light can then be collected and analyzed using a photodiode to determine the environmental pressure acting on the different holes of the probe.

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.

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.

A pressure sensing method includes providing a first receive antenna array that receives a first signal at a first frequency, providing a second receive antenna array that receives a second signal at a second frequency that differs from the first frequency, coupling a diode to the first receive antenna array and the second receive antenna array, coupling a transmit antenna array to the diode, receiving, by the diode, the first signal at the first frequency and the second signal at the second frequency, outputting, by the diode, a third signal at a third frequency that is a difference between the first frequency and the second frequency, receiving, by the transmit antenna array from the diode, the third signal at the third frequency, and outputting, by the transmit antenna array, the third signal at the third frequency.

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.

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.

Systems, methods, and apparatuses for taking pressure measurements are provided. A multi-hole pressure sensor probe can include a probe tip having a plurality of probe tip holes. The probe tip holes can lead to probe tip channels that convey fluid from the measurement environment to pressure transducers. The pressure transducers can operate using optical transduction techniques. A light source can be applied to the diaphragm, and the light reflected from the diaphragm changes as the position of the diaphragm changes. Further, a reflective material can be applied on the backside of the diaphragm to increase its reflective properties. The light can then be collected and analyzed using a photodiode to determine the environmental pressure acting on the different holes of the probe.

Systems, methods, and apparatuses for taking pressure measurements are provided. A multi-hole pressure sensor probe can include a probe tip having a plurality of probe tip holes. The probe tip holes can lead to probe tip channels that convey fluid from the measurement environment to pressure transducers. The pressure transducers can operate using optical transduction techniques. A light source can be applied to the diaphragm, and the light reflected from the diaphragm changes as the position of the diaphragm changes. Further, a reflective material can be applied on the backside of the diaphragm to increase its reflective properties. The light can then be collected and analyzed using a photodiode to determine the environmental pressure acting on the different holes of the probe.

An apparatus for measuring at least one of temperature and pressure within a cylinder of an internal combustion engine can include an engine valve and a sensor. The internal combustion engine can include a valvetrain having rocker arm assembly, a camshaft, a valve, and a hydraulic lash adjuster. The engine valve can have a valve head and a valve stem extending from the valve head in an axial direction. The valve head can have a valve face configured to be in pressure communication with an engine cylinder. The valve stem can have an outer surface with a cylindrical portion and a variably-shaped portion. The variably-shaped portion can define a target detectable by the sensor and the sensor can be installed adjacent to the target. Alternatively, the sensor can be positioned to detect a level of force at some point along the valvetrain.