Research Article  Open Access
Lei Chen, Ke Zhang, Xiangwei Zhu, Yangbo Huang, Gang Ou, Huicui Liu, "BeiDou Satellites Assistant Determination by Receiving Other GNSS Downlink Signals", International Journal of Antennas and Propagation, vol. 2016, Article ID 1413401, 10 pages, 2016. https://doi.org/10.1155/2016/1413401
BeiDou Satellites Assistant Determination by Receiving Other GNSS Downlink Signals
Abstract
GNSS’s orbit determinations always rely on ground station or intersatellite links (ISL). In the emergency of satellitetoground links and ISL breakoff, 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), carriertonoise ratio (), dilution of precision (GDOP), and geometric distance rootmeansquare (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 costeffective.
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 groundstation observing systems (GSOS) including the United Xband 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 groundstation 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].
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 abovementioned 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 Section 2, 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 (), the Doppler changing rate (), the minimum number of visible satellites (MNVS), the carriertonoise ratio (), the GDOP, and the geometric distance rootmeansquare (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 Section 2, 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 BDSB1, BDSB2, and BDSB3 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 outofband interference. The spectrum distribution diagram is shown in Figure 2.
As shown in Figure 2, among all the GNSS downlink signals, the signals carried on L2 band, including GPS L2C and GLONASS C/A signals, are far from the BDSB1, BDSB2, and BDSB3 bands; hence, GPS L2CBPSK() signal and GLONASS C/A CodeBPSK(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 BDSB2 band and 22.52 MHz away from center frequency of BDSB3 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 () is calculated as where is the electromagnetism shielding efficiency, which is about 110 dB for general cable and radio frequency components [10]; 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; is the band suppression of band pass filter (BPF) and when the signal is outofband, it can be up to 40 dB with a welldesigned narrowband BPF. Then of BDS is approximate to the received GNSS signal power: dBW = −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 Section 3, the signal receiving performance is analyzed by evaluating the Doppler frequency shift (), the Doppler changing rate (), the minimum number of visible satellites (MNVS), the carriertonoise ratio (), the GDOP, and the geometric distance rootmeansquare (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 Figure 1. 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 () can be obtained as shown in Table 1, where is the orbit altitude, is the transmitted downlink signal beamwidth, and is the earth shielding angle. In the available beamwidth ranges, the number of visible satellites (NVS), , , , GDOP, and gdrms changing trends are analyzed in this section.

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 () (unit: deg), beamwidth δθ (unit: deg), and . 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.
It is revealed in Figure 3 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 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 () and Doppler Changing Rate ()
The 1st and 2ndorder dynamics of the satellites result in drastic Doppler frequency shift () and Doppler changing rate (). 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, of received GPS and GLNOASS signals are simulated and shown in Figure 4. The first 24 hours’ simulation results are given as an example.
The ranges of 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 of on BDS’s MEO, GEO, and IGSO satellites are shown in Figure 5.
As shown in Figure 5, most 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 received on BDS MEO satellite varies sharply. The largest observed on MEO satellites is approximately −30 Hz/s since MEO has the highest dynamic. But most 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 is at least ±20 kHz for a high dynamic receiver and the acceptable 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. CarriertoNoise Ratio ()
Without considering antenna gain’s difference in different directions, the (unit: dBHz) can be calculated according to the receiver’s value (unit: dB/K) and the receiving power (unit: dBm):where = 1.38^{−23 }J/K is the Boltzmann constant and is the receiving antenna’s gain (unit: dB). is the equivalent isotropically radiated power (unit: dBm) of the transmitter, and the free space loss (unit: dB) is expressed aswhere is the carrier wavelength (unit: m) and is the distance between the GNSS satellites and the BDS satellites (unit: m).
is assumed to be 0 dB in this section for simplifying the understanding of the variations. The of GPS and GLONASS signals received on BDS MEO, GEO, and IGSO satellites are shown in Figure 6.
As shown in Figure 6, the 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 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.
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 receiving is above the threshold, the GPS and GLONASS signals may be received by BDS satellitesborne receivers. The receiving gain varies with the antenna’s configurations readwhere is the antenna efficiency and % in GPS. The approximate receiving antenna beamwidth () may be expressed aswhere is antenna’s aperture (unit: m). It is beneficial to improve by increasing the receiving gain of the antenna. However, a larger may result in a smaller , which degrades the NVS performance. Therefore, the tradeoff between and the 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 and the signal tracking periods. Hence, the constraint of is necessary to be proposed, and by simulating with different , 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 RootMeanSquare (gdrms)
A comprehensive factor is necessary for capturing the joint effects of MNVS, , and GDOP on the received satellite signal quality. The authors of [11] adopted distance rootmeansquare (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 :where is given aswhere is the clock broadcast error; is the ephemeris broadcast error; is the receiver’s noise resolution error; is the error from multipath effect (all units: m). in the spaceborne GNSS receiver, the effects of ionosphere and troposphere, which and are not exist. The typical values are shown in Table 2 [11].

The typical binary phase shift keying (BPSK) coarse acquisition (C/A) code receiver adopts an incoherent earlylate power mode delay lock loop (DLL) discriminator. can be calculated according to the actual code tracking accuracy: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.

4. Simulation and Parameters Optimization
The minimum gdrms is achieved by numerical simulations for the application. Since gdrms is determined by MNVS, , and GDOP. The search space for MNVS, , 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.
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, (beam’s starting elevation), and (beamwidth) is analyzed by simulations. The ranges of 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.
When and , the MNVS of the GNSS signal received on BDS MEO satellite is shown in Figure 9.
As shown in Figure 9, the maximum MNVS may be achieved in the range of and , where we have . In the range of and , the constraints of are satisfied.
Theoretically, increasing and decreasing allows more satellites to fall into the receiver’s antenna beam. However, the increasing leads to the reduction of . When the is below the threshold, it is unavailable for signal tracking and the MNVS is 0. Therefore, the simulation above has considered the limitation of threshold.
4.2. Simulation with Constraint of
Along with the constraint of MNVS, of GNSS signals are received on BDS MEO satellites where is in the ranges of and obeying the constraint dBHz. of the received satellite signal for different and is shown in Figure 10.
As shown in Figure 10, the maximum is achieved when deg and deg, where dBHz.
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 where is simulated by changing and . By obeying Constraint 3, . The variation of GDOP is shown in Figure 11.
In order to simplify the illustration, the GDOP values are set to be 0 on conditions of or dBHz or . As observed in Figure 11, the increase of results in the decrease of GDOP on BDS MEO satellite. The changing trend of is inverse to . According to the simulation, the valid ranges are limited to and . 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 of and , 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).
(a)
(b)
(c)
As shown in Figure 12, the gdrms of MEO becomes the least on = 40 deg and deg which is m. The least gdrms from the BDS GEO satellite occurred at conditions of = 10 deg and deg. The least gdrms from the BDS IGSO satellite was achieved when = 6 deg and deg.
At the same time, , GDOP, and MNVS values of the parameters are calculated in Table 4.

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 () and starting elevation () simulated before. The patterns of designed antennas are shown in Figure 13.
(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 Figure 13, the antennas patterns have lower gains in the direction towards the earth and form an annular beam in space. These designs make a larger 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, , GDOP, and gdrms are chosen as the evaluating parameters. The constraints have been determined for searching the optimal antenna performance. Then the optimal beamwidth () and starting elevation () 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.
Competing Interests
The authors declare that there is no conflict of interests regarding the publication of this paper.
Acknowledgments
The authors received financial aid from National Natural Science Foundation of China, Fund Code 41304026.
References
 C. Wen, M. Wang, L. Qi, D. Li, and Y. Qiu, “The application of the GNSS receiver in the third stage of china lunar exploration program,” in Proceedings of the 27th Conference of Spacecraft TT&C Technology in China, vol. 323 of Lecture Notes in Electrical Engineering, pp. 3–17, Springer, 2015. View at: Publisher Site  Google Scholar
 O. Balbach, B. Eissfeller, G. Hein, W. Enderle, M. Schmidhuber, and N. Lemke, “Tracking GPS above GPS satellite altitude: first results of the GPS experiment on the HEO mission equatorS,” in Proceeedings of the IEEE Position Location and Navigation Symposium, pp. 243–249, Palm Springs, Calif, USA, April 1998. View at: Publisher Site  Google Scholar
 M. Moreau, F. Bauer, J. Carpenter, E. Davis, G. Davis, and L. Jackson, “Preliminary results from of the GPS flight experiment on the high earth orbit AMSAT OSCAR 40 spacecraft,” in Proceedings of the 25th Annual AAS Rocky Montain Guidance and Control Conference, Guidance and Control, vol. 11 of Advance in the Astronautical Sciences, pp. 44–59, 2002. View at: Google Scholar
 M. Christian and L. Denis, “Realtime GEO orbit determination using TOPSTAR 3000 GPS receiver,” Navigation, vol. 48, no. 3, pp. 169–179, 2001. View at: Publisher Site  Google Scholar
 L. Qiao, S. Lim, and J. Liu, “Autonomous GEO satellite navigation with multiple GNSS measurements,” in Proceedings of the 22nd International Technical Meeting of the Satellite Division of the Institute of Navigation (ION GNSS '09), pp. 3611–3619, Savannah, Ga, USA, September 2009. View at: Google Scholar
 GPS ICD 200, ISGPS200 Revision D, IRN200D001: NAVSTAR global positioning system Interface Specification, NAVSTAR GPS Space Segment/Navigation User Interface, USA, 2006, http://www.gps.gov/technical/icwg/ISGPS200D.pdf.
 V. A. Menshikov and G. M. Solovyev, “Global Navigation Satellite System (GLONASS),” in Van Nostrand's Scientific Encyclopedia, 2006. View at: Publisher Site  Google Scholar
 Galileo_ICD_2010, European GNSS (Galileo) open service: signal in space: interface control document. Publications Office of the European Union, Issue 1, European GNSS, 2010, http://w3.uch.edu.tw/ccchang50/Galileo_ICD_2010.pdf.
 BDS ICD, “BeiDou navigation satellite system signal in space interface control document,” Open Service Signal Version 2.0. China Satellite Navigation Office, 2013. View at: Google Scholar
 J. W. Betz, Signal structure for satellitebased navigation past, present, and future, Inside GNSS, 2013, http://www.insidegnss.com.
 E. Kaplan and C. Hegarty, Understanding GPS Principles and Application, Artech House, 2nd edition, 2008.
 W. Parkinson and J. Spilker, Global Positioning System: Theory and Applications, Volume II, American Institute of Aeronautics and Astronautics, 1996. View at: Publisher Site
 L. Chen, Y. Huang, W. Liu, and G. Ou, “Feasibility analysis of GNSS multiconstellation positioning for lunar spacecraft,” in China Satellite Navigation Conference (CSNC) 2015 Proceedings: Volume I, vol. 340 of Lecture Notes in Electrical Engineering, pp. 749–763, 2015. View at: Publisher Site  Google Scholar
Copyright
Copyright © 2016 Lei Chen et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.