# Highly Sensitive Reentrant Cavity-Microstrip Patch Antenna Integrated Wireless Passive Pressure Sensor for High Temperature Applications

Authors: Fei Lu; Yanjie Guo; Qiulin Tan; Tanyong Wei; Guozhu Wu; Haixing Wang; Lei Zhang; Xiaowei Guo; Jijun Xiong
Journal: Journal of Sensors
 (2017)

---

## Abstract

A novel reentrant cavity-microstrip patch antenna integrated wireless passive pressure sensor was proposed in this paper for high temperature applications. The reentrant cavity was analyzed from aspects of distributed model and equivalent lumped circuit model, on the basis of which an optimal sensor structure integrated with a rectangular microstrip patch antenna was proposed to better transmit/receive wireless signals. In this paper, the proposed sensor was fabricated with high temperature resistant alumina ceramic and silver metalization with weld sealing, and it was measured in a hermetic metal tank with nitrogen pressure loading. It was verified that the sensor was highly sensitive, keeping stable performance up to 300 kPa with an average sensitivity of 981.8 kHz/kPa at temperature 25°C, while, for high temperature measurement, the sensor can operate properly under pressure of 60–120 kPa in the temperature range of 25–300°C with maximum pressure sensitivity of 179.2 kHz/kPa. In practical application, the proposed sensor is used in a method called table lookup with a maximum error of 5.78%.


---

## Body

## 1. Introduction

Wireless passive sensors are now in urgent research needs for application of extreme conditions, for example, high temperature, high speed of rotation, and high pressure. Like in aerospace, the development of aviation engines and gas turbines property, design evaluation, and performance monitoring are key factors which affect the development of the aerospace industry. For an engine, combustion chamber and turbine are the two core parts which need to survive at temperature up to 2000 K, of which the high temperature property directly affects the working efficiency and life of the engine [1]. By now, the engine inner parameters cannot be measured in situ directly due to the fact that most sensors cannot survive in high temperature for the limitation of materials, and they are often wire-connected to accomplish the whole sensing process. High temperature parameters are generally obtained indirectly via simulation from measurement results in external environment.There are lots of challenges for sensing devices in the development of engine. Conventional test methods require wire connections between the test controller and each test node and the wires are connected with specific signal disposal circuits, causing problems like wire layout, power supply, electromagnetic interference, transmission range, transmission security, and high temperature resistance. Hence, the wireless and passive sensing devices are in an increasing need for extreme conditions. By now, there are generally three kinds of wireless sensing technology, that is, near-field inductance sensing (LC) technology, surface acoustic wave (SAW) sensing technology, and microwave scattering (RF) signal reading technology. Fonseca proposed a LC resonance based pressure sensor which operated up to 5 bar in temperature range of 25–400°C [2]. It was fabricated in LTCC ceramic with low profile and high integration. Tan et al. proposed LC based sensor which can realize temperature and pressure measurement simultaneously, providing temperature compensation for pressure, making it precise for the measurement of the pressure at high temperature [3]. But the lumped circuit has low Q factor, causing a rapid reduction of the stored energy and a short wireless transmission distance [4, 5]. For LGS (La3Ga5SiO14, one of piezoelectric materials) based SAW sensor, it could survive up to 1400°C, but there are several factors that limit potential use of it, including excessive conductive and viscous losses, deviations from stoichiometry, and chemical instability [6]. Moreover, LGS based sensor has significant loss in the radio frequency spectrum, making it hard to work in high frequency [7], while, for microwave scattering technology, it has advantages of high Q factor and stability in high frequency. In addition, microwave scattering based sensor is not easy to be disturbed by ambient environment for its metal closed structure. Xiong et al. proposed a resonator based wireless temperature sensor which is fabricated in alumina ceramic, realizing temperature measurement up to 800°C [4]. But due to the closed cylindrical volume of the sensor, the dimension is not small enough to make it integrated with measured object. Afterwards, Cheng et al. designed a low-profile temperature sensor based on planar patch resonator which can realize temperature measurement up to 1050°C [8]. And for pressure measurement, Zhao innovatively proposed a wireless passive sensing technique based on evanescent-mode cavity resonator, successfully demonstrating airflow and displacement measurements by integrating an UWB monopole antenna [9]. But the sensor was not fabricated in high temperature resistant material. Hence, it can just work in normal environment. Cheng et al. fabricated a cylindrical resonator based pressure sensor for wireless pressure measurement up to 5 N at 1000°C [8]. But the pressure was loaded manually via a dielectric rod, not realizing a contactless measurement. It is not suitable for the aforementioned extreme conditions.Here we proposed a wireless passive pressure sensor composed of a reentrant cavity with an aperture and a rectangular microstrip patch antenna which can operate properly up to 300°C. It was designed in microwave scattering and fabricated in high temperature resistant alumina ceramic with silver metalization. To verify the validity of the pressure sensor, it was firstly tested in a metal-sealed tank with nitrogen load. It was shown that the sensor was well operated up to 3 bar in 25°C with a high average sensitivity of 981.8 kHz/kPa, realizing a contactless measurement for pressure. Then it was tested up to 300°C and had a maximum sensitivity of 179.2 kHz/kPa which was many times higher than the LC based sensor proposed in [10] and SAW based sensor in [11]. It was promising to be used for inner engine pressure measurement in the near future for farther research, realizing a real sense of contactless measurement in harsh environment.


## 2. Design, Characterization, and Fabrication of the Sensor

Reentrant cavity is a tunable microwave resonator which is characterized with a smaller dimension at the same frequency as general cylindrical resonator. For an equivalent cavity model, it is difficult to be accurately calculated using Maxwell’s equations. But when the cavity model dimension meets the conditiond≪h, as shown in Figure 1(a), and the geometric dimension is smaller than the resonant wavelength, we can assume that the high frequency electric field of the cavity dominant mode TM010 is mainly distributed among the space with height d, while the magnetic field is distributed around the embedded cylinder which presents annular concentration [12–14] as shown in Figure 1(a). So we obtain the equivalent lumped circuit model in electrostatic field by analysis of the distributed model according to [15]. The equivalent shunt circuit model is shown in Figure 1(b). L is the equivalent annular inductor and C is the equivalent capacitor which is composed of two parts C0 and C1. C0 is the capacitance between the inner post top and the center section of the cap which is a parallel-plate capacitor, while C1 is the capacitance between the post side wall and the end plate. R is the equivalent resistor of the cavity.Figure 1
(a) Electromagnetic field distribution of the stimulated reentrant cavity. (b) Equivalent shunt lumped circuit model.
(a)
(b)C
0 can be calculated according to the parallel-plate capacitor expression as(1)C0=ε0πr02d,where ε0 is the permittivity in vacuum, denoting an approximate value of 8.854×10-12 F/m, r0 is the radius of the inner post, andd is the distance between the cap and the top of the post. Here we ignore the fringe effect of the parallel-plate capacitor for purpose of simplification of the calculation while causing little influence on the analysis. And C1 can be expressed according to Green’s theorem as [16](2)C1=4ε0r0ln⁡eh2+r1-r022d,where r1 denotes outer radius of the cavity. The equivalent capacitor C of the reentrant cavity is calculated as(3)C=C0+C1.And the equivalent inductorL can be expressed as [16](4)L=μ0h2πln⁡r1r0,where μ0 is the permeability in vacuum, denoting 4π×10-7 H/m. Here L can be seen as a one-turn annular inductor with cross-section (h-d)×(r1-r0) [16].From the above expressions, (1)–(4), the resonant frequency of the reentrant cavity can be calculated as(5)f0=12πLC=c2πr0hr02d-2πln⁡2deh2+r1-r02ln⁡r1r0-1/2.Accordingly, the quality factor of reentrant cavityQ is approximately given by [17](6)1Q=δ1h+h-d/r0h+1/r12ln⁡r1/r0,where δ denotes skin depth of specific metallic conductor and it is related to resonant frequency f0 and can be expressed as(7)δ=22πμ0σf0,where σ denotes conductivity of metallic conductor, as for Dupont 6142D silver used for the fabrication of the sensor in the experiment, it is 6.1×107 S/m.It can be known from the above analysis that a reentrant cavity is an all-metal-sealed structure which is sensitive to deformation in section with heightd, but it cannot realize signal interaction with external wireless interrogation antenna. Thus a rectangular aperture needs to be punched to make the internal electromagnetic wave wirelessly coupled with an interrogation antenna. Because the aperture is small in dimension, it makes little perturbation on the electromagnetic field distribution and the resonant frequency of the cavity dominant resonant mode. This was verified by us via Ansoft HFSS software. When the cavity was wirelessly interrogated with an external antenna, one of the electromagnetic wave components transmitted by the interrogation antenna with the same frequency as the reentrant cavity resonant frequency forms standing wave inside the cavity and gradually oscillates till it disappears, while the electromagnetic wave components in other frequencies were reflected to the antenna. Hence, there is frequency deficiency for the received signal compared with the transmitted signal. By analysis of the S parameters of the interrogation antenna, the cavity resonant frequency can be obtained. As shown in Figure 2, the signal process system can be seen as a two-port network. Here we use S(1,1) parameter of the antenna as an evaluation of the signal strength, and the corresponding frequency where valley lies is the resonant frequency of the reentrant cavity sensor.Figure 2
Two-port network signal transmission mechanism.To make the cavity preferably receive signals transmitted from the interrogation antenna, a reply antenna was designed. A microstrip patch antenna was integrated on the cavity top covering the couple aperture to act as an “intermediary agent” between the antenna and the cavity. It can receive the interrogation signal from the antenna and in turn transmits the response signal of the sensor to the antenna. Based on above analysis, a reentrant cavity-microstrip patch antenna integrated pressure sensor structure based on alumina ceramic substrate and silver paste was designed in Figure3.Figure 3
Mechanical structure of the reentrant cavity sensor. (a) Cross-section view of the assembled sensor. (b) Top view of the sensor cap. (c) Bottom view of the cap. (d) Cross-section view of the cap. (e) Cross-section view of the substrate.
(a)
(b)
(c)
(d)
(e)For the proposed reentrant cavity structure, pressure sensitive part is the cap, as shown in Figure3(d). When there is uniformly distributed load imposed on the top surface, the cap is deformed inside the cavity, causing the distance d to decrease. Thus the equivalent capacitor C of the cavity increases, leading a reduced resonant frequency. We can obtain the measured pressure value via a corresponding relationship between the pressure and sensor resonant frequency. Here the small deflection theory for a round-clamped thin plate was used to analyze the deformation condition of the sensor cap as shown in Figure 4.Figure 4
Deformed cap with pressure load.The maximum central deformation of the plate can be expressed as [18](8)d0=0.01512Pr141-ν2Et3,where E is Young’s modulus of the deformed material, ν is Poisson’s ratio, and t is the thickness of the cap. For alumina ceramic we used, the specific properties are listed in Table 1.Table 1
Alumina ceramic properties (provided by Bolandi Machinery Equipment Co. Ltd.).
Property
Value
Density (g/cm3)
3.9
Flexure strength (MPa)
450
Young’s modulus (GPa)
390
Permittivity
10
Poisson’s ratio
0.22According to expressions (5) and (8), the sensitivity of the sensor can be calculated as(9)Sd=∂f∂d=f0dC0′d+C1′d.To determine the sensor dimension and further analyze the sensitivity of the pressure deformable reentrant cavity, we preset the sensor model with three different configurations and the relationship betweend and resonant frequency was simulated in MATLAB as shown in Figure 5(a). The slope of each curve is seen as S(d). But the deformed cap is a curved surface with maximum deflection in center. It is not exactly in accordance with the flat-cap reentrant cavity. Qualitative analysis was used to evaluate the sensitivity of the sensor and determine the dimension.Figure 5
(a) Resonant frequency variation with distanced for three sensor configurations. (b) Q factor variation with d.
(a)
(b)It can be seen from Figure5(a) that the sensor sensitivity is influenced by both the inner post radius r0 and h. Generally, the resonant frequency variation is more evident under the same pressure when r0 and h are smaller, respectively, especially when d is smaller than 0.2 mm. The sensor Q factor variation with d was plotted in Figure 5(b). It can be seen that the Q factor decreases with the decrease of d. The tendency is especially distinct when d is smaller than 0.1 mm. For practical measurement, the higher the Q factor is, the further the sensor signal can wirelessly transfer. So there needs to be a tradeoff between the sensor sensitivity and Q factor. The final dimension of the sensor was listed in Table 2.Table 2
Dimension of the sensor (mm).
Symbol
Value
r
0
5
r
1
15
h
19.5
d
1
r
2
20
h
2
24.5
h
1
0.3
w
1
22
l
1
30
w
2
1.5
l
2
22
s
2For the dimension design of the pressure deformable cap, Ansoft ANSYS software was utilized to analyze the deformation and stress of the pressure loaded plate. A circular thin plate with radius of 20 mm and thickness of 0.3 mm was finally determined as the sensor cap. ANSYS simulation was shown in Figure6. We can see that the maximum central deflection is 0.949 mm when the plate is loaded with 3.5 bar uniform pressure, and the maximum stress occurred along the circumference of the cap which is 344 MPa. It is smaller than the alumina allowable flexure strength of 450 MPa. Hence, the sensor can be operated in a safe pressure range of 0–3.5 bar.Figure 6
(a) Deformation distribution of the cap with 3.5 bar pressure loaded on the sensor. (b) Von Mises stress distribution.
(a)
(b)For fabrication of the sensor, a sealed cavity with metalization inside the ceramic wall is needed. It is hard to be realized with existing processing craft. So we fabricated the sensor for separated two parts, that is, the cap and substrate, and then bonded them with welding method. Specific fabrication processes are shown in Figure7. Firstly, a substrate mould was fabricated in advance for shaping of liquid alumina precursor. A precursor is generally composed of organic monomer, crosslinking agent, dispersant, initiator, and catalyst. Then the mould filled with precursor was placed at high temperature until the precursor got hard to be solid. Thirdly, the striped precursor was placed in a furnace for sintering above 1000°C to make the ceramic structure dense and harder. Fourthly, ceramic fine machining, for example, cutting, milling, and polishing, was carried out to fabricate the sensor substrate as our designed dimension. Fifthly, silver was printed on the inner wall of the cavity and specific antenna pattern was printed on the cap as we have designed. It needs to be noted that the thickness of the printed silver should be no less than 12 um to prevent skin effect at high frequency. Then the silver printed substrate was placed in furnace for sintering up to 850°C. The cap was fabricated by the same process as above. Finally, the sensor cap and substrate were bonded together through high temperature welding method, that is, melting the silver between the contact surface and then cooling it to be hard. The fabrication process of the sensor after fine machining is shown in Figure 8.Figure 7
Fabrication processes of the reentrant cavity-microstrip patch antenna integrated sensor.Figure 8
Sensor physical structure. (a) Sensor cap after fine machining. (b) Top view of the sensor cap. (c) Back view of the sensor cap. (d) Sensor substrate after fine machining. (e) Sensor substrate with silver printed in the inner wall. (f) Assembled sensor.
(a)
(b)
(c)
(d)
(e)
(f)


## 3. Measurement of the Sensor

To verify the validity and sensitivity of the fabricated sensor, the sensor was firstly measured in a metal-hermetic tank with uniform nitrogen pressure load as shown in Figure9. A PCB based CPW (coplanar waveguide) interrogation antenna connected with a VNA (Agilent vector network analyzer 5061B) via a coaxial cable was used. In metal tank, electromagnetic waves, either transmitted signal or response signal, would be reflected by the metal wall. Therefore, a rubber electromagnetic wave absorber RAT-2G-3 mm was pasted on the inner metal wall, which can absorb incident waves in 2 GHz center frequency with maximum vertical reflection of −10 dB. To further increase the signal-to-noise ratio (SNR) of the sensor, Time Domain Gating algorithm was used via VNA; the tested results are shown in Figure 10(a).Figure 9
System for sensor pressure measurement at 25°C.Figure 10
(a) Frequency variation with pressure from 0.25 bar to 3 bar at 25°C. (b) Extracted resonant frequencies under different pressure at 25°C.
(a)
(b)The pressure was loaded from 0.25 bar to 3 bar at an increased step of 0.25 bar. And the corresponding frequencies of each negative peak were extracted and plotted in Figure10(b). When the pressure increased from 0.25 bar to 3 bar, the resonant frequency varied from 2.03 GHz to 1.76 GHz, presenting an approximately linear relationship with the loaded pressure. An average sensitivity of 981.8 kHz/kPa was calculated to be 50 times greater than the LC based wireless sensor proposed in [3]. But the measured resonant frequency, 2.39 GHz, of the sensor with no pressure load was deviated from the simulated frequency, 1.719 GHz; this is mainly due to the calculation error of the equivalent lumped model, the electromagnetic field distribution error caused by the punched aperture, and the process error during the fabrication.The sensor was verified to be valid with pressure load; thus measurement at high temperature was carried on. The measurement system was shown in Figure11. A waveguide coaxial adapter was used as an interrogation antenna to survive in higher temperature. Moreover, the operating temperature range of the absorber is 25–200°C. It cannot survive over 200°C. For our measurement system, there is thermal resistant material (mullite) along the round of the heat plate to make the absorber insulated with high temperature. And the environment temperature that the absorber lies in is under 100°C even when the heat plate is above 300°C. The distance between the sensor and the interrogation antenna is 12 mm.Figure 11
System for sensor pressure measurement at high temperature.Temperature in range 25–300°C with an increasing step of 50°C was set for six phases. For every phase, temperature increasing time was 15 mins and the holding time was 10 mins. During the holding time, the sensor was loaded with gas pressure from 60 to 120 kPa at a step of 20 kPa. The measured curves for resonant frequency versusS(1,1) were plotted in Figures 12(a) and 12(b) at 25°C and 300°C, respectively. We can see that the resonant frequency decreased with the increase of the pressure when the temperature was constant. The tendency was still obvious up to 300°C. Then the resonant frequencies at different temperatures and under different pressures were extracted and plotted in Figure 12(c). For a constant temperature, it showed an approximately linear relationship between the pressure and the measured resonant frequency, proving the sensor to be effective under high temperature. The linear fitted slopes and intercepts of the measured curves at different temperatures are listed in Table 3.Table 3
Linear fitted slopes and intercepts of the measured pressure at different temperatures.
Temperature (°C)
Slope (GHz/kPa)
Intercept (GHz)
25
−0.17
2.4063
100
−0.17875
2.4144
150
−0.18
2.42364
200
−0.15625
2.43288
250
−0.11063
2.43274
300
−0.1225
2.43765Figure 12
(a) Resonant frequency versusS(1,1) under pressure of 60–120 kPa at 25°C and (b) 300°C. (c) Pressure versus resonant frequency at temperature from 25°C to 300°C. (d) Referenced pressure versus pressure obtained by table lookup.
(a)
(b)
(c)
(d)The function relation between the slopes and the temperatures is quantic-polynomial-fitted as(10)S=A0+A1T1+A2T2+A3T3+A4T4+A5T5,where T is the temperature, S are slopes in Figure 12(c), A0=-0.15788, A1=-8.12415×10-4, A2=1.72278×10-5, A3=-1.85942×10-7, A4=8.79068×10-10, and A5=-1.38742×10-12.However, the function relation between intercepts and temperatures is quartic-polynomial-fitted as(11)I=B0+B1T1+B2T2+B3T3+B4T4,whereI represents intercepts in Figure 12(c), B0=2.41373, B1=-4.60615×10-4, B2=7.41625×10-6, B3=-3.25863×10-8, and B4=4.6213×10-11.We can see that there is a one-to-one relationship between each temperature and the correspondent linear function which can be determined using (10) and (11). For practical application, the pressure can be obtained relying on a method called table lookup on the premise that the temperature is measured in advance via methods proposed in [3–5]. It can be seen from Figure 12(d) that the pressure obtained by table lookup is around the referenced pressure with a maximum error of 5.78%. It should be noted that the problem of seal between the sensor cap and substrate is one of the key factors to realize higher temperature measurement for pressure. In this paper, alumina ceramic is able to survive up to 1500°C and silver 900°C. But here we did not utilize them to the temperature limitation due to the fact that the melting sealing method can just realize surface physical bonding for silver-ceramic contact, while, in temperature above 300°C, the difference of thermal expansion coefficient between the two materials is even greater, leading to mismatch in stress; thus the melting welding surface cannot be stably sealed. This is adverse to the gas pressure loading for our contactless measurement. Consequently, our further research will be focused on the settlement of sealing problem.


## 4. Conclusions

The reentrant cavity-microstrip patch antenna integrated pressure sensor based on alumina ceramic presented in this paper is used for wireless telemetry at high temperature. Both the sensor distribution model and equivalent lumped circuit model were analyzed for the design of the sensor dimension. For measurement, Time Domain Gating algorithm was used via VNA in process of the sensor signal, effectively raising the SNR of the sensor response signal. The fabricated sensor was operated properly with gas pressure loaded up to 3 bar at 25°C with average sensitivity of 981.8 kHz/kPa, proving the validity of the pressure sensor structure. And for high temperature measurement, the sensor was tested under pressure of 60–120 kPa in temperature range of 25–300°C with maximum pressure sensitivity of 179.2 kHz/kPa. For further improvement of the sensor properties, for example, ability of higher temperature resistance and higher operation stability, the sealing problem under high temperature needs to urgently be solved in the future. For instance, rapidly developed HTCC technology is promising to be used later for its advantages of high integration in structure and makes it easy to realize a hermetic cavity structure. This is meaningful for future pressure telemetry in situ under harsh environment.



---

*Source: 3417562-2017-10-19.xml*