A Solar Antenna for Aeronautical Internal
Communications and Tracking-Made Possible by
MEMS AC Power Battery
Anthony Amoah, Bao Jingfu
University of Electronic Science and Technology of China
Abstract-A novel solar antenna has been designed and
simulated using high frequency simulating software (HFSS) for
effective aeronautical internal communications. Energy efficient
MEMS AC power battery which sits on the heart of the solar
antenna and will operate at a centre frequency of 5.516GHz
within the band 5470- 5725MHz. The calculated pull-down
voltage of the battery was approximately 1959.77V and a charge
of 0.026 Coulombs. The voltage standing wave ratio at
5.5160GHz was 1.160 and Wi-Fi 5G (5180-5850 MHz)
I. INTRODUCTION
Figure 1. The Solar Antenna with the MEMS battery
A modernized GPS for civil applications will provide
quality of service for aeronautical radio navigation service in
band L5-1176.45MHz and 1575MHz to improve aviation
safety applications [1-5]. Recently, there have been reports of
missing flights, power failure and communication failures in
the airplanes. ITU in its World Radio Conference 2015[6]
allocated frequency bands 5150-5250 MHz, 5250-5350 MHz
and 5470-5725 MHz for the implementation of mobile
wireless access systems (WAS) including radio local area
networks (RLANS) for aeronautical services. This paper
therefore unfolds its novelties on efficient AC MEMS power
battery on solar antenna for effective internal communications
in the airplane and tracking as well serve as an alternative Figure 2. The MEMS battery on the Antenna
second emergency locator transmitter (ELT) with
omnidirectional characteristics with different frequency bands.
III. SIMULATION RESULTS AND ANALYSIS
II. DESIGN
dB(S(WAVEPORT_AT,WAVEPORT_AT)
XY Plot 17 HFSSDesign1 ANSOFT
A solar antenna technology with the integration of RF 0.00 Curve Info
dB(S(WAVEPORT_AT,WAVEPORT_AT))
Microelectromechanical systems (MEMS) AC battery is -5.00
Setup1 : Sw eep
designed to sit directly on the heart of the solar antenna as
-10.00
shown in Figure 1. The total spring constant (ka) is given by:
-15.00
ka 32Ewt 3 / l 3 8V 1 v tw / l (1)
-20.00
-25.00
-30.00
0.00 2.00 4.00 6.00 8.00 10.00 12.00 14.00
Freq [GHz]
Figure 3.The Simulated result of the Antenna
,(((
TABLE I satellite is at a frequency of 1575MHz. The modernized GPS
VOLTAGE STANDING WAVE RATIO ON THE ANTENNA for civil applications with a new frequency also provide
quality of service for aeronautical radio navigation service
Freq [GHz]
V SWR(WA V EPORT_A T)
Setup1 : Sw eep
(ARNS) in band L5-1176.45MHz to improve aviation safety
1
2
0.116000
0.216000
9.271809
8.439654
as well as L1 which is 1575MHz.
3 0.316000 8.446781
4 0.416000 8.484738
5 0.516000 8.274088
6 0.616000 7.730595
7 0.716000 6.893244
8 0.816000 5.844515
9 0.916000 4.733858
10 1.016000 3.690633
11 1.116000 2.823733
12 1.216000 2.203750
13 1.316000 1.871667
14 1.416000 1.838936
15 1.516000 2.027090
16 1.616000 2.313880
17 1.716000 2.610927
18 1.816000 2.860384
19 1.916000 3.021499
20 2.016000 3.067475
21 2.116000 2.988359
22 2.216000 2.794796
23 2.316000 2.517428
TABLE II
THE VOLTAGE STANDING WAVE RATIO ON THE ANTENNA Figure 4. . The Gain Total
Figure 5 shows the magnitude of directivity in decibel which
Freq [GHz ]
V SWR(WA V EPORT_A T)
Setup1 : Sw eep
is the measure of how directional the solar antenna’s radiation
47
48
4.716000
4.816000
1.527758
1.550862 pattern is. That is, with relative to the energy of an isotropic
antenna in the peak direction of radiation, the solar antenna’s
49 4.916000 1.547247
50 5.016000 1.517710
51 5.116000 1.465187
52
53
5.216000
5.316000
1.394762
1.313220
energy is 6.8764 times that of an isotropic antenna. Figure
54
55
5.416000
5.516000
1.229855
1.160823
shows the gain at left hand circular polarization of the
56
57
5.616000
5.716000
1.138034
1.179850 Antenna.
58 5.816000 1.254754
59 5.916000 1.335203
60 6.016000 1.407978
61 6.116000 1.466792
62 6.216000 1.509683
63 6.316000 1.537572
64 6.416000 1.546476
65 6.516000 1.500318
66 6.616000 1.404395
67 6.716000 1.291980
68 6.816000 1.191318
69 6.916000 1.118476
TABLE III
THE VOLTAGE STANDING WAVE RATIO ON THE ANTENNA
V SWR(WA V EPORT_A T)
Freq [GHz]
Setup1 : Sw eep
117 11.716000 1.993549
118 11.816000 2.072601
119 11.916000 2.129893
120 12.016000 2.132739 Figure 5 The Magnitude of Directivity Total
121 12.116000 2.032561
122 12.216000 1.818223
123 12.316000 1.689272
124 12.416000 1.840109 The figures 5 and 6 show the magnitude of directivity and
125 12.516000 2.035414
126 12.616000 2.090989 the gain in decibel at right hand circular polarization (RHCP)
127 12.716000 1.911164
128 12.816000 1.488550 and left hand circular polarization (LHCP). Figure 5 shows the
magnitude of the total directivity of the solar antenna and also
129 12.916000 2.396288
130 13.016000 2.260608
131
132
13.116000
13.216000
2.388167
2.779343 describes the 3-D left hand circular polarization gain. Figure 7
133
134
13.316000
13.416000
2.177065
1.743297
describes the 3-D right hand circular polarization gain.
135 13.516000 1.656653
136 13.616000 2.006801
137 13.716000 1.616638
138 13.816000 2.118012
139 13.916000 2.290277
The solar antenna was designed on a microstrip. Figure 4
illustrate the total gain in decibel with the minimum gain to be
-63.575 decibel and the maximum gain to be -40.236 decibel
which are approximately 2.171 mW and 1.3412 mW of power
respectively. At the frequency of 5.5160 GHz, the voltage
standing wave ratio is 1.16 and a loss of -21 decibel (0.7 mW).
The GPS receives position information of flights from the Figure 6.The Gain at LHCP
IV. CONCLUSION
A novel solar antenna with a MEMS AC battery has been
designed and simulated for internal communications in the
Airplane for services and tracking. The solar antenna was
design to operate at 5.5 GHz. The Aeronautical Radio
navigation and Aeronautical Mobile Airport Communications
(AeroMACS) operating within 1.350 GHz to 1.370 GHz and
5150-5250 MHz respectively who have these frequencies
Figure 7. The Gain at RHCP within the simulated results. Air Traffic Control will have
greater advantage because of the needless supply of voltage
TABLE III for the solar antennas and systems. Since the ATC or Ground
DESIGN PARAMETERS OF THE SOLAR ANTENNA to Air Communication System transceivers use about 50
Name Material Width Length Thickness/ carrier frequencies with RF power of 50W modulated in
(mm) (mm) (mm) Height digital mode, these MEMS AC power batteries will help
(mm) serve as many radios as needed.
Substrate 1 Silicon 100 460 5 ACKNOWLEDGMENT
Ground Aluminium 100 460 1
Radiating Cobalt 100 400 0.4
This work was supported by the National Natural Science
element
Foundation of China and the China Academy of Engineering
Transmission Aluminium 10 60 0.0005
Physics (U143012).
line REFERENCES
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TABLE IV signal L2C and L5, 2009 second international conference on computer
DESIGN PARAMETERS OF THE MEMS AC BATTERY ON THE SOLAR and electrical engineering, Dubai, Arab Emirates, pp. 412-415,
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