# BeiDou Satellites Assistant Determination by Receiving Other GNSS Downlink Signals

Authors: Lei Chen; Ke Zhang; Xiangwei Zhu; Yangbo Huang; Gang Ou; Huicui Liu
Journal: International Journal of Antennas and Propagation
 (2016)

---

## Abstract

GNSS’s orbit determinations always rely on ground station or intersatellite links (ISL). In the emergency of satellite-to-ground links and ISL break-off, BeiDou navigation satellite system (BDS) satellites cannot determine their orbits. In this paper, we propose to add a spaceborne annular beam antenna for receiving the global positioning system (GPS) and global navigation satellite system (GLONASS) signals; therefore, the BDS satellites may be capable of determining their orbits by GPS/GLONASS signals. Firstly, the spectrum selection, the power isolation, the range of Doppler frequency shift, and changing rate are taken into account for the feasibility. Specifically, the L2 band signals are chosen for receiving and processing in order to prevent the overlapping of the receiving and transmitting signals. Secondly, the minimum number of visible satellites (MNVS), carrier-to-noise ratio (C
/
N
0), dilution of precision (GDOP), and geometric distance root-mean-square (gdrms) are evaluated for acquiring the effective receiving antennas’ coverage ranges. Finally, the scheme of deploying 3 receiving antennas is proved to be optimal by analysis and simulations over the middle earth orbit (MEO), geostationary earth orbit (GEO), and the inclined geosynchronous satellite orbit (IGSO). The antennas’ structures and patterns are designed to draw a conclusion that installing GPS and GLONASS receivers on BDS satellites for emergent orbits determination is cost-effective.


---

## Body

## 1. Introduction

With the rapid developing of the global navigation satellite system (GNSS), satellites’ orbit determination becomes a problem as it can only be measured from ground-station observing systems (GSOS) including the United X-band tracking telemetering and control system (UXB) and very long baseline interferometry (VLBI). The predicted orbital parameters can be injected into the satellites by a huge terrestrial uploading antenna. For the satellites beyond the ground-station observing systems’ tracking telemetry and command (TT&C) ranges, the intersatellite links (ISL) established on BeiDou navigation satellite system (BDS) or global positioning system (GPS) can be used for relay transmissions.However, GSOS are complex and expensive to be maintained, while ISL is susceptible to jamming, which prevents the GNSS from continuing broadcast accurate navigation signals. To possess the ability of orbit determination without supporting by the GSOS and ISL, we propose to install onboard GNSS receiver on BDS satellites for receiving navigation signals from other GNSSs. By receiving navigation signals from GPS, Galileo, or global navigation satellite system (GLONASS), the BDS satellites’ orbit may be determined in order to ensure the accuracy of the broadcasted BDS signal as well as maintaining other functions uninterruptedly. The proposed scheme, BDS orbit determination by GPS/GLONASS (BODGG), requires simpler maintenance, lower cost than the GSOS/ISL solutions. Also, the BODGG scheme is less influenced by the atmosphere (error caused by troposphere and ionosphere).The spaceborne GPS receivers have been widely used on low earth orbit (LEO) spacecraft, where the height of LEO is lower than the height of GPS’s orbit. GPS signals transmit towards the earth so that the LEO spacecrafts can easily receive the signals for positioning ‎[1]. While the high earth orbit (HEO) spacecrafts such as the geostationary earth orbit (GEO) satellites and the inclined geosynchronous satellite orbit (IGSO) satellites can hardly receive GPS’s or others GNSS’s downlink signals since they are higher than the navigation satellites, and a solution is to receive the leaked signals from the side lobe beams of the GPS satellite’s transmitting antennas. As shown in Figure 1, the above solution is based on the fact that the GPS antenna contains a main lobe beam towards the earth and a side lobe beam towards the space around the earth. However, a challenge is brought about as the signals emitted from the side lobe may be too weak to be effectively utilized by the HEO satellites ‎[2].Figure 1
Diagrammatic sketch of GPS and HEO/IGSO satellites’ position.In order to address the above challenges, Moreau and Christian have analyzed the visibility of GNSS satellites observed from GEO ‎[3, 4]. Qiao et al. have calculated the geometric dilution of precision (GDOP) of the received GNSS signals on GEO satellites ‎[5]. However, the solutions in ‎[3–5] did not take into account the fact that a GNSS satellite needs to simultaneously transmit navigation signals to provide localization services as well as receiving navigation signals for locating itself. Therefore, the second challenge to be dealt with is to support simultaneously receiving GNSS signals and transmitting BDS signals, since the receivers installed on BDS satellites may be easily interfered by the downlink signals transmitted from themselves.Against the background, we propose to address the above-mentioned two challenges in this paper, where the BDS satellites operate on GEO, IGSO, and MEO; the feasibility of GNSS side lobe signals received by BDS satellites on the 3 orbits is analyzed. The rest is organized as follows. In Section2, the appropriate receivable signals are chosen, and the isolation budget is calculated. In Section 3, the signal receiving performance is analyzed by evaluating the Doppler frequency shift (f
d), the Doppler changing rate (d
f
d
/
d
t), the minimum number of visible satellites (MNVS), the carrier-to-noise ratio (C
/
N
0), the GDOP, and the geometric distance root-mean-square (gdrms). In Section 4, the optimal antenna beamwidth and elevation are obtained numerically. In Section 5, the GNSS signal receiving antennas of GEO, IGSO, and MEO BDS satellites are designed and conclusions are provided in Section 6.


## 2. Spectrum Selection and Isolation Analysis

In Section2, the appropriate receivable signals are chosen, and the isolation budget is calculated.According to the interface control documents (ICD) of GPS ICD 200 ‎[6], GLONASS ICD ‎[7], Galileo_ICD_2010 ‎[8], and BDS ICD ‎[9], the level of spectrum overlapping for different navigation system is high. The signal frequency chosen for BDS satellites orbit determination should be different from the transmitting signal frequencies on BDS-B1, BDS-B2, and BDS-B3 bands in order to avoid the electromagnetic interference. Hence, the bandwidth of the signal receiving channel at the receiver should be narrowed in order to ensure the band suppression by filtering the out-of-band interference. The spectrum distribution diagram is shown in Figure 2.Figure 2
Spectrum distribution diagram of GNSS.As shown in Figure2, among all the GNSS downlink signals, the signals carried on L2 band, including GPS L2-C and GLONASS C/A signals, are far from the BDS-B1, BDS-B2, and BDS-B3 bands; hence, GPS L2C-BPSK(1) signal and GLONASS C/A Code-BPSK(0.511) signal are most appropriate for receiving the BDS satellites’ orbit determination. These two signals are narrowband, which are 20.46 MHz away from BDS-B2 band and 22.52 MHz away from center frequency of BDS-B3 band. According to ‎[10], QZSS satellites of Japan will also broadcast a signal on the same band of GPS L2 to enhance the open signal, and it will benefit the double signals receiving. Since these bands have been used by the GPS and GLONASS, other systems such as IRNSS and SBAS will not occupy these bands. The analyses of the electromagnetic leakage and shielding effectiveness of the BDS satellites are given below.The BDS satellites’ downlink signal power is about 20 dBW (equal to 50 dBm) ‎[9] which is strongly amplified and directed toward the earth, while the downlink signals transmitted from other GNSS satellites on the other side of the earth are so weak and submerged in the noise. Therefore, the low noise amplifier (LNA) operates in saturation mode if the transmitted BDS signal leaks into its receiving channel. The nonlinear effect caused by the LNA prevents the receiver from acquiring and tracking the normal GNSS signals. Therefore, the budget of leaked transmitted signal power (P
1) is calculated as (1)
P
1
=
P
t
-
L
s
-
L
c
-
L
b
p
f
=
-
130
d
B
m
,where L
s is the electromagnetism shielding efficiency, which is about 110 dB for general cable and radio frequency components ‎[10]; L
c is the coupling loss of the leaked transmitted signal from the space to the receiving antenna, which may be as low as 40 dB if the antenna installing position and direction are well tuned; L
b
p
f is the band suppression of band pass filter (BPF) and when the signal is out-of-band, it can be up to 40 dB with a well-designed narrowband BPF. Then P
1 of BDS is approximate to the received GNSS signal power: P
r
=
-
175dBW = −145 dBm. Thus, by choosing the L2 band downlink signals of GPS and GLONASS, the receiver can suffer from the B2 and B3 signals from BDS satellites themselves.


## 3. Signal Receiving Performance Analysis

In Section3, the signal receiving performance is analyzed by evaluating the Doppler frequency shift (f
d), the Doppler changing rate (d
f
d
/
d
t), the minimum number of visible satellites (MNVS), the carrier-to-noise ratio (C
/
N
0), the GDOP, and the geometric distance root-mean-square (gdrms).According to the geometrical relations of BDS satellites and the earth in the aerospace, the space is shaded by the earth on the range of ±13.2 deg from the satellite on MEO, as the blue section in Figure1. And it is ±8.7 deg from the satellite on GEO or IGSO. Then the designed transmitting antenna beam widths are ±13.5 deg, ±9.5 deg, and ±9.5 deg for BDS MEO, IGSO, and GEO satellites, respectively. Therefore, the range of available receiving beamwidth (θ
r) can be obtained as shown in Table 1, where H is the orbit altitude, θ
t is the transmitted downlink signal beamwidth, and θ
s is the earth shielding angle. In the available beamwidth ranges, the number of visible satellites (NVS), f
d, d
f
d
/
d
t, C
/
N
0, GDOP, and gdrms changing trends are analyzed in this section.Table 1
Beam coverage of BDS satellites’ antenna.
Orbits
H [m]
θ
t [deg]
θ
s [deg]
θ
r [deg]
MEO
21528000
±13.5
±13.2
>13.2 or <−13.2
IGSO
35786000
±9.5
±8.7
>8.7 or <−8.7
GEO
35786000
±9.5
±8.7
>8.7 or <−8.7


### 3.1. Number of Visible Satellites (NVS)

NVS is defined as the number of visible satellites during the whole time with the constraints on beam’s starting elevation (θ
0) (unit: deg), beamwidth δθ (unit: deg), and C
/
N
0. Based on the definition of ICD files and ephemeris of GPS and GLONASS, the simulation model is generated with 24 GPS satellites and 24 GLNOASS satellites. The simulation runs for 7 days and Figure 3 illustrates the NVS performance of the BDS’s MEO, GEO, and IGSO satellites.Figure 3
NVS changing trend from BDS MEO, GEO, and IGSO satellites.It is revealed in Figure3 that the NVS performance satisfies the demand of BDS satellite positioning on MEO, GEO, and IGSO during the whole simulation time without considering the beamwidth (δθ) and C
/
N
0 threshold of satellite’s receiving antenna. The altitudes of the GEO and the IGSO are higher than that of the MEO; hence, the NVS observed by the GEO or IGSO satellites is higher. Specifically, the average NVS is 35.7, 33, and 20.1 on GEO, IGSO, and MEO, respectively.In order to acquire the unambiguous positions of the satellite, the NVS should not be smaller than 4 ‎[11]. In the following, we will evaluate the minimum number of visible satellites defined as minimum NVS (MNVS).


### 3.2. Doppler Frequency Shift (f
d) and Doppler Changing Rate (d
f
d
/
d
t)

The 1st- and 2nd-order dynamics of the satellites result in drastic Doppler frequency shift (f
d) and Doppler changing rate (d
f
d
/
d
t). The ranges of the dynamic property should be calculated for evaluating the demands BDS satellites borne receiver.For BDS satellites on MEO, GEO, and IGSO,f
d of received GPS and GLNOASS signals are simulated and shown in Figure 4. The first 24 hours’ simulation results are given as an example.Figure 4
f
d of GLNOASS and GPS signals received on BDS satellites.The ranges off
d on IGSO and MEO are more violent than that on GEO, because the GEO satellite is relatively static to the earth so that the relative speed towards GPS and GLONASS satellites is also less than that of the BDS MEO or IGSO satellites.The simulation results ofd
f
d
/
d
t on BDS’s MEO, GEO, and IGSO satellites are shown in Figure 5.Figure 5
Thed
f
d
/
d
t of GPS and GLNOASS signals observed from BDS’s satellites.As shown in Figure5, most d
f
d
/
d
t values are negative, which indicates the fact that the parting velocity is larger than the approach velocity in most of time. The GNSS signal’s d
f
d
/
d
t received on BDS MEO satellite varies sharply. The largest d
f
d
/
d
t observed on MEO satellites is approximately −30 Hz/s since MEO has the highest dynamic. But most d
f
d
/
d
t values fall within the range of −5 Hz/s to 3 Hz/s on MEO; from −2 Hz/s to 2 Hz/s on GEO, and from −3 Hz/s to 3 Hz/s on IGSO.According to ‎[11], the acceptable f
d is at least ±20 kHz for a high dynamic receiver and the acceptable d
f
d
/
d
t is at least ±10 Hz/s. By taking them as the Doppler tracking threshold and the Doppler changing rate threshold, spaceborne GPS and GLONASS receivers are feasible for the dynamic calculated above.


### 3.3. Carrier-to-Noise Ratio (C
/
N
0)

Without considering antenna gain’s difference in different directions, theC
/
N
0 (unit: dB-Hz) can be calculated according to the receiver’s G
r
/
T
d
B value (unit: dB/K) and the receiving power P
r (unit: dBm):(2)
C
N
0
=
P
E
I
R
P
-
L
d
+
G
r
+
G
r
T
d
B
-
k
,where k = 1.38−23J/K is the Boltzmann constant and G
r is the receiving antenna’s gain (unit: dB). P
E
I
R
P is the equivalent isotropically radiated power (unit: dBm) of the transmitter, and the free space loss (unit: dB) L
d is expressed as(3)
L
d
=
20
lg
⁡
λ
4
π
R
,where λ is the carrier wavelength (unit: m) and R is the distance between the GNSS satellites and the BDS satellites (unit: m).G
r is assumed to be 0 dB in this section for simplifying the understanding of the C
/
N
0 variations. The C
/
N
0 of GPS and GLONASS signals received on BDS MEO, GEO, and IGSO satellites are shown in Figure 6.Figure 6
C
/
N
0 of GPS and GLONASS signals received on BDS satellites.As shown in Figure6, the C
/
N
0 of the signals received on MEO is largest since the BDS MEO satellites are nearest to the GPS and the GLONASS satellites, which are also operating on MEO. The C
/
N
0 on BDS GEO and IGSO are close as they have similar altitudes.Actually, the directional transmitting downlink antenna has a main lobe toward the earth and a side lobe toward the space around the earth. According to ‎[12], the gain of transmitting antenna pattern may be obtained, as shown in Figure 7.Figure 7
The downlink antenna pattern of GPS satellite (90 deg elevation).Compared with the main lobe gain of the GPS downlink antenna, the gain attenuation of the side lobe is about 15 dB. The 3 dB beamwidth of its main lobe defined by GPS approaches the off axis angle relative to nadir. The signals transmitted from the side lobe are defined in the space service volume (SSV) of GPS ICD file where the lowest GPS III signal powers received on GEO are −186.0 dBW for the P(Y) code and −183.0 dBW for the C/A code.When the receiver and transmitter are located on different sides of the earth, the receivers may be within the pattern’s coverage of transmitting antenna. When the signal receivingC
/
N
0 is above the threshold, the GPS and GLONASS signals may be received by BDS satellites-borne receivers. The receiving gain G
r varies with the antenna’s configurations read(4)
G
r
d
B
=
10
lg
⁡
π
D
λ
2
η
d
B
,where η is the antenna efficiency and η
≈
50% in GPS. The approximate receiving antenna beamwidth (δ
θ) may be expressed as(5)
δ
θ
≈
52
λ
D
,where D is antenna’s aperture (unit: m). It is beneficial to improve C
/
N
0 by increasing the receiving gain of the antenna. However, a larger G
r may result in a smaller δ
θ, which degrades the NVS performance. Therefore, the tradeoff between δ
θ and the G
r should be carefully struck, as we will show below.The transmitting signals from GPS and GLONASS are designed and operated by other governments so that they cannot be changed by users. We can only change the receiving antenna on BDS in the future, to optimal C
/
N
0 and the signal tracking periods. Hence, the constraint of C
/
N
0 is necessary to be proposed, and by simulating with different δ
θ, the optimal value can be sought out.


### 3.4. Dilution of Precision (GDOP)

The GDOP value represents the deviation’s amplification of the measurement’s error attributed to solution position equations. GDOP is related to the constellation geometrical configuration and the receiver position. The GDOP may be readily calculated according to ‎[13]. The formulas are left out here.


### 3.5. United Constraint of Geometric Distance Root-Mean-Square (gdrms)

A comprehensive factor is necessary for capturing the joint effects of MNVS,C
/
N
0, and GDOP on the received satellite signal quality. The authors of ‎[11] adopted distance root-mean-square (drms) to measure the horizontal error in topocentric coordinate system. Motivated by ‎[11], we focus on space positioning and proposed gdrms as the unified metric considering both the GDOP and the σ
U
E
R
E:(6)
g
d
r
m
s
=
G
D
O
P
×
σ
U
E
R
E
,where σ
U
E
R
E is given as(7)
σ
U
E
R
E
=
σ
t
2
+
σ
e
2
+
σ
i
n
p
h
2
+
σ
e
p
h
2
+
σ
r
e
c
2
+
σ
m
u
l
t
2
,where σ
t is the clock broadcast error; σ
e is the ephemeris broadcast error; σ
r
e
c is the receiver’s noise resolution error; σ
m
u
l
t is the error from multipath effect (all units: m). in the spaceborne GNSS receiver, the effects of ionosphere and troposphere, which σ
i
n
p
h and σ
e
p
h are not exist. The typical values are shown in Table 2 ‎[11].Table 2
Typical URER budget for GPS.
Segment
Error source
1σ error [m]
Space/control
σ
t
1.1
σ
e
0.8
User
σ
i
n
p
h
0.1 (nonexistent here)
σ
e
p
h
0.2 (nonexistent here)
σ
r
e
c
0.1 (related toC
/
N
0)
σ
m
u
l
t
0.2
Pseudo range error
Total (RSS)
1.4The typical binary phase shift keying (BPSK) coarse acquisition (C/A) code receiver adopts an incoherent early-late power mode delay lock loop (DLL) discriminator.σ
r
e
c can be calculated according to the actual code tracking accuracy:(8)
σ
rec-tDLL
≈
B
n
2
C
/
N
0
D
1
+
2
T
2
-
D
C
/
N
0
,
D
≥
π
R
c
B
f
e
,
B
n
2
C
/
N
0
1
B
f
e
T
c
+
B
f
e
T
c
π
-
1
D
-
1
B
f
e
T
c
2
1
+
2
T
2
-
D
C
/
N
0
,
R
c
B
f
e
≤
D
<
π
R
c
B
f
e
,
B
n
2
C
/
N
0
1
B
f
e
T
c
1
+
1
T
·
C
/
N
0
,
D
<
R
c
B
f
e
.The meanings and typical values of the parameters are shown in Table 3. According to those formulas above, the unified gdrms may be chosen as the optimized objective in the optimal receiving antenna design.Table 3
Glossary list.
Symbol
Typical value
Unit
Meaning
B
n
0.2
MHz
Bandwidth
D
0.5
chip
Early-late code correlator spacing
T
0.02
s
Preintegration time
R
c
1.023
MHz
Code rate
B
f
e
2
R
c
MHz
Front-end bandwidth
T
c
1
/
R
c
s
Code period


## 3.1. Number of Visible Satellites (NVS)

NVS is defined as the number of visible satellites during the whole time with the constraints on beam’s starting elevation (θ
0) (unit: deg), beamwidth δθ (unit: deg), and C
/
N
0. Based on the definition of ICD files and ephemeris of GPS and GLONASS, the simulation model is generated with 24 GPS satellites and 24 GLNOASS satellites. The simulation runs for 7 days and Figure 3 illustrates the NVS performance of the BDS’s MEO, GEO, and IGSO satellites.Figure 3
NVS changing trend from BDS MEO, GEO, and IGSO satellites.It is revealed in Figure3 that the NVS performance satisfies the demand of BDS satellite positioning on MEO, GEO, and IGSO during the whole simulation time without considering the beamwidth (δθ) and C
/
N
0 threshold of satellite’s receiving antenna. The altitudes of the GEO and the IGSO are higher than that of the MEO; hence, the NVS observed by the GEO or IGSO satellites is higher. Specifically, the average NVS is 35.7, 33, and 20.1 on GEO, IGSO, and MEO, respectively.In order to acquire the unambiguous positions of the satellite, the NVS should not be smaller than 4 ‎[11]. In the following, we will evaluate the minimum number of visible satellites defined as minimum NVS (MNVS).


## 3.2. Doppler Frequency Shift (f
d) and Doppler Changing Rate (d
f
d
/
d
t)

The 1st- and 2nd-order dynamics of the satellites result in drastic Doppler frequency shift (f
d) and Doppler changing rate (d
f
d
/
d
t). The ranges of the dynamic property should be calculated for evaluating the demands BDS satellites borne receiver.For BDS satellites on MEO, GEO, and IGSO,f
d of received GPS and GLNOASS signals are simulated and shown in Figure 4. The first 24 hours’ simulation results are given as an example.Figure 4
f
d of GLNOASS and GPS signals received on BDS satellites.The ranges off
d on IGSO and MEO are more violent than that on GEO, because the GEO satellite is relatively static to the earth so that the relative speed towards GPS and GLONASS satellites is also less than that of the BDS MEO or IGSO satellites.The simulation results ofd
f
d
/
d
t on BDS’s MEO, GEO, and IGSO satellites are shown in Figure 5.Figure 5
Thed
f
d
/
d
t of GPS and GLNOASS signals observed from BDS’s satellites.As shown in Figure5, most d
f
d
/
d
t values are negative, which indicates the fact that the parting velocity is larger than the approach velocity in most of time. The GNSS signal’s d
f
d
/
d
t received on BDS MEO satellite varies sharply. The largest d
f
d
/
d
t observed on MEO satellites is approximately −30 Hz/s since MEO has the highest dynamic. But most d
f
d
/
d
t values fall within the range of −5 Hz/s to 3 Hz/s on MEO; from −2 Hz/s to 2 Hz/s on GEO, and from −3 Hz/s to 3 Hz/s on IGSO.According to ‎[11], the acceptable f
d is at least ±20 kHz for a high dynamic receiver and the acceptable d
f
d
/
d
t is at least ±10 Hz/s. By taking them as the Doppler tracking threshold and the Doppler changing rate threshold, spaceborne GPS and GLONASS receivers are feasible for the dynamic calculated above.


## 3.3. Carrier-to-Noise Ratio (C
/
N
0)

Without considering antenna gain’s difference in different directions, theC
/
N
0 (unit: dB-Hz) can be calculated according to the receiver’s G
r
/
T
d
B value (unit: dB/K) and the receiving power P
r (unit: dBm):(2)
C
N
0
=
P
E
I
R
P
-
L
d
+
G
r
+
G
r
T
d
B
-
k
,where k = 1.38−23J/K is the Boltzmann constant and G
r is the receiving antenna’s gain (unit: dB). P
E
I
R
P is the equivalent isotropically radiated power (unit: dBm) of the transmitter, and the free space loss (unit: dB) L
d is expressed as(3)
L
d
=
20
lg
⁡
λ
4
π
R
,where λ is the carrier wavelength (unit: m) and R is the distance between the GNSS satellites and the BDS satellites (unit: m).G
r is assumed to be 0 dB in this section for simplifying the understanding of the C
/
N
0 variations. The C
/
N
0 of GPS and GLONASS signals received on BDS MEO, GEO, and IGSO satellites are shown in Figure 6.Figure 6
C
/
N
0 of GPS and GLONASS signals received on BDS satellites.As shown in Figure6, the C
/
N
0 of the signals received on MEO is largest since the BDS MEO satellites are nearest to the GPS and the GLONASS satellites, which are also operating on MEO. The C
/
N
0 on BDS GEO and IGSO are close as they have similar altitudes.Actually, the directional transmitting downlink antenna has a main lobe toward the earth and a side lobe toward the space around the earth. According to ‎[12], the gain of transmitting antenna pattern may be obtained, as shown in Figure 7.Figure 7
The downlink antenna pattern of GPS satellite (90 deg elevation).Compared with the main lobe gain of the GPS downlink antenna, the gain attenuation of the side lobe is about 15 dB. The 3 dB beamwidth of its main lobe defined by GPS approaches the off axis angle relative to nadir. The signals transmitted from the side lobe are defined in the space service volume (SSV) of GPS ICD file where the lowest GPS III signal powers received on GEO are −186.0 dBW for the P(Y) code and −183.0 dBW for the C/A code.When the receiver and transmitter are located on different sides of the earth, the receivers may be within the pattern’s coverage of transmitting antenna. When the signal receivingC
/
N
0 is above the threshold, the GPS and GLONASS signals may be received by BDS satellites-borne receivers. The receiving gain G
r varies with the antenna’s configurations read(4)
G
r
d
B
=
10
lg
⁡
π
D
λ
2
η
d
B
,where η is the antenna efficiency and η
≈
50% in GPS. The approximate receiving antenna beamwidth (δ
θ) may be expressed as(5)
δ
θ
≈
52
λ
D
,where D is antenna’s aperture (unit: m). It is beneficial to improve C
/
N
0 by increasing the receiving gain of the antenna. However, a larger G
r may result in a smaller δ
θ, which degrades the NVS performance. Therefore, the tradeoff between δ
θ and the G
r should be carefully struck, as we will show below.The transmitting signals from GPS and GLONASS are designed and operated by other governments so that they cannot be changed by users. We can only change the receiving antenna on BDS in the future, to optimal C
/
N
0 and the signal tracking periods. Hence, the constraint of C
/
N
0 is necessary to be proposed, and by simulating with different δ
θ, the optimal value can be sought out.


## 3.4. Dilution of Precision (GDOP)

The GDOP value represents the deviation’s amplification of the measurement’s error attributed to solution position equations. GDOP is related to the constellation geometrical configuration and the receiver position. The GDOP may be readily calculated according to ‎[13]. The formulas are left out here.


## 3.5. United Constraint of Geometric Distance Root-Mean-Square (gdrms)

A comprehensive factor is necessary for capturing the joint effects of MNVS,C
/
N
0, and GDOP on the received satellite signal quality. The authors of ‎[11] adopted distance root-mean-square (drms) to measure the horizontal error in topocentric coordinate system. Motivated by ‎[11], we focus on space positioning and proposed gdrms as the unified metric considering both the GDOP and the σ
U
E
R
E:(6)
g
d
r
m
s
=
G
D
O
P
×
σ
U
E
R
E
,where σ
U
E
R
E is given as(7)
σ
U
E
R
E
=
σ
t
2
+
σ
e
2
+
σ
i
n
p
h
2
+
σ
e
p
h
2
+
σ
r
e
c
2
+
σ
m
u
l
t
2
,where σ
t is the clock broadcast error; σ
e is the ephemeris broadcast error; σ
r
e
c is the receiver’s noise resolution error; σ
m
u
l
t is the error from multipath effect (all units: m). in the spaceborne GNSS receiver, the effects of ionosphere and troposphere, which σ
i
n
p
h and σ
e
p
h are not exist. The typical values are shown in Table 2 ‎[11].Table 2
Typical URER budget for GPS.
Segment
Error source
1σ error [m]
Space/control
σ
t
1.1
σ
e
0.8
User
σ
i
n
p
h
0.1 (nonexistent here)
σ
e
p
h
0.2 (nonexistent here)
σ
r
e
c
0.1 (related toC
/
N
0)
σ
m
u
l
t
0.2
Pseudo range error
Total (RSS)
1.4The typical binary phase shift keying (BPSK) coarse acquisition (C/A) code receiver adopts an incoherent early-late power mode delay lock loop (DLL) discriminator.σ
r
e
c can be calculated according to the actual code tracking accuracy:(8)
σ
rec-tDLL
≈
B
n
2
C
/
N
0
D
1
+
2
T
2
-
D
C
/
N
0
,
D
≥
π
R
c
B
f
e
,
B
n
2
C
/
N
0
1
B
f
e
T
c
+
B
f
e
T
c
π
-
1
D
-
1
B
f
e
T
c
2
1
+
2
T
2
-
D
C
/
N
0
,
R
c
B
f
e
≤
D
<
π
R
c
B
f
e
,
B
n
2
C
/
N
0
1
B
f
e
T
c
1
+
1
T
·
C
/
N
0
,
D
<
R
c
B
f
e
.The meanings and typical values of the parameters are shown in Table 3. According to those formulas above, the unified gdrms may be chosen as the optimized objective in the optimal receiving antenna design.Table 3
Glossary list.
Symbol
Typical value
Unit
Meaning
B
n
0.2
MHz
Bandwidth
D
0.5
chip
Early-late code correlator spacing
T
0.02
s
Preintegration time
R
c
1.023
MHz
Code rate
B
f
e
2
R
c
MHz
Front-end bandwidth
T
c
1
/
R
c
s
Code period


## 4. Simulation and Parameters Optimization

The minimum gdrms is achieved by numerical simulations for the application. Since gdrms is determined by MNVS,C
/
N
0, and GDOP. The search space for MNVS, C
/
N
0, and GDOP are given in Figure 8, where the minimum gdrms is derived and the optimal antenna beam parameters may be acquired by numerical searching.Figure 8
Flowchart of simulation and analysis.For GNSS signal receivers and the receiving antennas installed on MEO, GEO, and IGSO BDS satellites, the simulation is implemented by software STK and MATLAB with GPS and GLONASS’s ephemeris for a BDS orbit’s period of seven days.


### 4.1. Simulation with Constraint of MNVS

Taking MEO as an example, the interplay of the MNVS,θ
0 (beam’s starting elevation), and  δ
θ (beamwidth) is analyzed by simulations. The ranges of (
δ
θ
+
θ
0
)
≤
72 deg within the GNSS transmitting antenna’s coverage, while the normal direction is defined to 90 deg, and the tangential direction is defined to 0 deg.Whenθ
0
∈
[
0,72
] and δ
θ
∈
[
5,72
-
θ
0
], the MNVS of the GNSS signal received on BDS MEO satellite (
f
M
N
V
S
M
E
O
(
θ
0
,
δ
θ
)
) is shown in Figure 9.Figure 9
MNVS observed from MEO satellite.As shown in Figure9, the maximum MNVS may be achieved in the range of θ
0
∈
[
31,40
] and δ
θ
∈
[
29,41
], where we have f
M
N
V
S
M
E
O
θ
0
,
δ
θ
m
a
x
=
13. In the range of θ
0
∈
[
0,52
] and δ
θ
∈
[
13,72
], the constraints of f
M
N
V
S
M
E
O
(
θ
0
,
δ
θ
)
≥
4 are satisfied.Theoretically, increasingδ
θ and decreasing θ
0 allows more satellites to fall into the receiver’s antenna beam. However, the increasing  δ
θleads to the reduction of C
/
N
0. When the C
/
N
0 is below the threshold, it is unavailable for signal tracking and the MNVS is 0. Therefore, the simulation above has considered the limitation of C
/
N
0 threshold.


### 4.2. Simulation with Constraint ofC
/
N
0

Along with the constraint of MNVS,C
/
N
0 of GNSS signals are received on BDS MEO satellites where f
C
/
N
0
M
E
O
(
θ
0
,
δ
θ
) is in the ranges of θ
0
∈
[
0,52
] and δ
θ
∈
[
13,72
] obeying the constraint f
C
/
N
0
M
E
O
(
θ
0
,
δ
θ
)
≥
30 dB-Hz. C
/
N
0 of the received satellite signal for different θ
0 and  δ
θ is shown in Figure 10.Figure 10
C
/
N
0 observed on MEO satellite.As shown in Figure10, the maximum C
/
N
0 is achieved when θ
0
=
45 deg and δ
θ
=
14 deg, where f
C
/
N
0
M
E
O
θ
0
,
δ
θ
m
a
x
=
50.63 dB-Hz.


### 4.3. Simulation with Constraint of GDOP

Combined with Constraint 1 and Constraint 2, the GDOP of GNSS signals are received by BDS satellite on MEO wheref
G
D
O
P
(
θ
0
,
δ
θ
) is simulated by changing θ
0 and δ
θ. By obeying Constraint 3, f
G
D
O
P
(
θ
0
,
δ
θ
)
<
10. The variation of GDOP is shown in Figure 11.Figure 11
GDOP observed on MEO satellite.In order to simplify the illustration, the GDOP values are set to be 0 on conditions off
G
D
O
P
M
E
O
(
θ
0
,
δ
θ
)
>
20 or f
C
/
N
0
M
E
O
(
θ
0
,
δ
θ
)
<
30 dB-Hz or f
M
N
V
S
M
E
O
(
θ
0
,
δ
θ
)
<
4. As observed in Figure 11, the increase of δ
θ results in the decrease of GDOP on BDS MEO satellite. The changing trend of f
G
D
O
P
M
E
O
(
θ
0
,
δ
θ
) is inverse to f
C
/
N
0
M
E
O
(
θ
0
,
δ
θ
). According to the simulation, the valid ranges are limited to θ
0
∈
[
0,52
] and δ
θ
∈
[
19,72
]. GDOP values observed in these ranges meet “Constraint 3.”


### 4.4. Simulation with Constraint of gdrms

For the BDS MEO satellite, the gdrms is calculated within the ranges ofθ
0
∈
[
0,53
] and δ
θ
∈
[
19,72
], as shown in Figure 12(a). Similarly, the gdrms of the BDS satellites on GEO and IGSO may also be simulated and optimized for the receiving antenna design. The gdrms of the received GNSS signal on the BDS GEO and IGSO satellites are illustrated in Figures 12(b) and 12(c).Figure 12
The gdrms changing trend of GNSS signal received from the BDS satellites. (a) Observed on MEO satellite. (b) Observed on GEO satellite. (c) Observed on IGSO satellite.
(a)
(b)
(c)As shown in Figure12, the gdrms of MEO becomes the least on θ
0 = 40 deg and δ
θ
=
33 deg which is f
g
d
r
m
s
M
E
O
θ
0
,
δ
θ
m
i
n
=
f
g
d
r
m
s
M
E
O
(
40,33
)
=
5.6843 m. The least gdrms from the BDS GEO satellite occurred at conditions of θ
0 = 10 deg and δ
θ
=
54 deg. The least gdrms from the BDS IGSO satellite was achieved when θ
0 = 6 deg and δ
θ
=
61 deg.At the same time,C
/
N
0, GDOP, and MNVS values of the parameters are calculated in Table 4.Table 4
Observations on BDS MEO, GEO, and IGSO satellites.
Parameter
On MEO
On GEO
On IGSO
gdrms [m]
5.6843
1.8886
1.9266
C
/
N
0 [dB-Hz]
42.6535
38.7638
38.7017
GDOP
3.9376
1.2126
1.2349
MNVS
13
19
19
(θ
0
,
δ
θ
) [deg]
(
40,33
)
(
10,54
)
(
6,61
)All the observed parameters satisfied the 3 constraints and meet the demand of BDS satellite positioning.


## 4.1. Simulation with Constraint of MNVS

Taking MEO as an example, the interplay of the MNVS,θ
0 (beam’s starting elevation), and  δ
θ (beamwidth) is analyzed by simulations. The ranges of (
δ
θ
+
θ
0
)
≤
72 deg within the GNSS transmitting antenna’s coverage, while the normal direction is defined to 90 deg, and the tangential direction is defined to 0 deg.Whenθ
0
∈
[
0,72
] and δ
θ
∈
[
5,72
-
θ
0
], the MNVS of the GNSS signal received on BDS MEO satellite (
f
M
N
V
S
M
E
O
(
θ
0
,
δ
θ
)
) is shown in Figure 9.Figure 9
MNVS observed from MEO satellite.As shown in Figure9, the maximum MNVS may be achieved in the range of θ
0
∈
[
31,40
] and δ
θ
∈
[
29,41
], where we have f
M
N
V
S
M
E
O
θ
0
,
δ
θ
m
a
x
=
13. In the range of θ
0
∈
[
0,52
] and δ
θ
∈
[
13,72
], the constraints of f
M
N
V
S
M
E
O
(
θ
0
,
δ
θ
)
≥
4 are satisfied.Theoretically, increasingδ
θ and decreasing θ
0 allows more satellites to fall into the receiver’s antenna beam. However, the increasing  δ
θleads to the reduction of C
/
N
0. When the C
/
N
0 is below the threshold, it is unavailable for signal tracking and the MNVS is 0. Therefore, the simulation above has considered the limitation of C
/
N
0 threshold.


## 4.2. Simulation with Constraint ofC
/
N
0

Along with the constraint of MNVS,C
/
N
0 of GNSS signals are received on BDS MEO satellites where f
C
/
N
0
M
E
O
(
θ
0
,
δ
θ
) is in the ranges of θ
0
∈
[
0,52
] and δ
θ
∈
[
13,72
] obeying the constraint f
C
/
N
0
M
E
O
(
θ
0
,
δ
θ
)
≥
30 dB-Hz. C
/
N
0 of the received satellite signal for different θ
0 and  δ
θ is shown in Figure 10.Figure 10
C
/
N
0 observed on MEO satellite.As shown in Figure10, the maximum C
/
N
0 is achieved when θ
0
=
45 deg and δ
θ
=
14 deg, where f
C
/
N
0
M
E
O
θ
0
,
δ
θ
m
a
x
=
50.63 dB-Hz.


## 4.3. Simulation with Constraint of GDOP

Combined with Constraint 1 and Constraint 2, the GDOP of GNSS signals are received by BDS satellite on MEO wheref
G
D
O
P
(
θ
0
,
δ
θ
) is simulated by changing θ
0 and δ
θ. By obeying Constraint 3, f
G
D
O
P
(
θ
0
,
δ
θ
)
<
10. The variation of GDOP is shown in Figure 11.Figure 11
GDOP observed on MEO satellite.In order to simplify the illustration, the GDOP values are set to be 0 on conditions off
G
D
O
P
M
E
O
(
θ
0
,
δ
θ
)
>
20 or f
C
/
N
0
M
E
O
(
θ
0
,
δ
θ
)
<
30 dB-Hz or f
M
N
V
S
M
E
O
(
θ
0
,
δ
θ
)
<
4. As observed in Figure 11, the increase of δ
θ results in the decrease of GDOP on BDS MEO satellite. The changing trend of f
G
D
O
P
M
E
O
(
θ
0
,
δ
θ
) is inverse to f
C
/
N
0
M
E
O
(
θ
0
,
δ
θ
). According to the simulation, the valid ranges are limited to θ
0
∈
[
0,52
] and δ
θ
∈
[
19,72
]. GDOP values observed in these ranges meet “Constraint 3.”


## 4.4. Simulation with Constraint of gdrms

For the BDS MEO satellite, the gdrms is calculated within the ranges ofθ
0
∈
[
0,53
] and δ
θ
∈
[
19,72
], as shown in Figure 12(a). Similarly, the gdrms of the BDS satellites on GEO and IGSO may also be simulated and optimized for the receiving antenna design. The gdrms of the received GNSS signal on the BDS GEO and IGSO satellites are illustrated in Figures 12(b) and 12(c).Figure 12
The gdrms changing trend of GNSS signal received from the BDS satellites. (a) Observed on MEO satellite. (b) Observed on GEO satellite. (c) Observed on IGSO satellite.
(a)
(b)
(c)As shown in Figure12, the gdrms of MEO becomes the least on θ
0 = 40 deg and δ
θ
=
33 deg which is f
g
d
r
m
s
M
E
O
θ
0
,
δ
θ
m
i
n
=
f
g
d
r
m
s
M
E
O
(
40,33
)
=
5.6843 m. The least gdrms from the BDS GEO satellite occurred at conditions of θ
0 = 10 deg and δ
θ
=
54 deg. The least gdrms from the BDS IGSO satellite was achieved when θ
0 = 6 deg and δ
θ
=
61 deg.At the same time,C
/
N
0, GDOP, and MNVS values of the parameters are calculated in Table 4.Table 4
Observations on BDS MEO, GEO, and IGSO satellites.
Parameter
On MEO
On GEO
On IGSO
gdrms [m]
5.6843
1.8886
1.9266
C
/
N
0 [dB-Hz]
42.6535
38.7638
38.7017
GDOP
3.9376
1.2126
1.2349
MNVS
13
19
19
(θ
0
,
δ
θ
) [deg]
(
40,33
)
(
10,54
)
(
6,61
)All the observed parameters satisfied the 3 constraints and meet the demand of BDS satellite positioning.


## 5. Designs of BDS Satellites’ Receiving Antennas

With the help of simulating software, CST Microwave Studio, the GNSS signals receiving antennas on BDS MEO, GEO, and IGSO satellites can be designed and simulated according to the optimal antenna beamwidth (δ
θ) and starting elevation (θ
0) simulated before. The patterns of designed antennas are shown in Figure 13.Figure 13
GNSS signal receiving antenna pattern on BDS satellites. (a) Antenna on MEO satellite. (b) Antenna on GEO satellite. (c) Antenna on IGSO satellite.
(a)
(b)
(c)The beam of antenna on MEO satellite covers the range from 40 deg to 73 deg on elevation, while that on GEO and IGSO satellites covers the range from 10 deg to 64 deg and from 6 deg to 67 deg, respectively. It is shown that the antenna on IGSO requires the largest beamwidth for covering enough satellites in order to obtain advanced performance.As shown in Figure13, the antennas patterns have lower gains in the direction towards the earth and form an annular beam in space. These designs make a larger G
r towards GNSS satellites in space around the earth than the general omnidirectional antenna. It may provide a better antijamming performance against the possible jamming signals coming from the earth.


## 6. Summary

In this paper, we propose novel orbit determination methods for BDS satellites with the aid of GPS and GLONASS signals. Two GPS and GLONASS signals on L2 band are chosen to avoid interference by the BDS’s transmitting signals. By analysis and simulations, MNVS,C
/
N
0, GDOP, and gdrms are chosen as the evaluating parameters. The constraints have been determined for searching the optimal antenna performance. Then the optimal beamwidth (δ
θ) and starting elevation (θ
0) are obtained. With the optimization objective of minimum gdrms, BDS MEO satellites reach the minimum gdrms of 5.6843 m when the beam coverage is 40~73 deg on elevation; BDS GEO satellites reach the minimum gdrms of 1.8886 m when the beam coverage is 10~64 deg on elevation; BDS IGSO satellites reach the minimum gdrms of 1.9266 m when the beam coverage is 6~67 deg on elevation. Finally, three antennas on BDS MEO, GEO, and IGSO satellites are designed. These contributions may be readily applied to the next generation BDS satellites.



---

*Source: 1413401-2016-07-11.xml*