• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    System and procedure for the determination of satellite orbits that allows, on the one hand, the reception of the signal transmitted by a reflector element and, on the other hand, the signal transmitted directly from the satellite and/or the satellite signal transmitted by another reflector element, a homodyne and/or heterodyne reception of the received signals is obtained and a set of orbital elements and/or a satellite state vector is obtained through a digital data processing module. of the interferometric phase of the received signals. (Machine-translation by Google Translate, not legally binding)
    公开号:ES2692175A1
    申请号:ES201730749
    申请日:2017-05-31
    公开日:2018-11-30
    发明作者:Antonio BROQUETAS IBARS；Roger MARTIN FUSTER；Marc FERNÁNDEZ USÓN；Germán Angel GRIMALDO SÁNCHEZ
    申请人:Universitat Politecnica de Catalunya UPC；
    IPC主号:
    专利说明:

    image 1
    image2
    image3
    image4
    image5
    image6


    - Reception by one of the antennas of the signal transmitted by a reflector element and by the other antenna of the signal transmitted by another reflector element or of the radio frequency signal emitted by the satellite;
    - Homodyne reception, through the homodyne reception device, which includes the following 5 sub-steps:
    o Consistent demodulation of the signal received by the antennas or of the combination of the signals received by the baseband antennas;
    o Obtaining the components in phase and quadrature of the baseband signal; I
    10 -Heterodyne reception, through the heterodyne reception device, which includes the following sub-steps:
    o Transfer at intermediate frequency of the signal received by the antennas or of the combination of the signals received by the antennas;
    o Consistent demodulation of the signal at intermediate frequency to baseband; 15 o Obtaining the components in phase and quadrature of the baseband signal.
    - Digitization of the components in phase and quadrature obtained, through the digital data processing module;
    - Filtering of the digital signal in the working band in the satellite baseband, through the digital data processing module;
    20-Obtaining the complex cross correlation of the filtered digital signals and / or the complex autocorrelation of a filtered digital signal with this same filtered digital signal with different temporal displacements, through the digital data processing module;
    - Obtaining the interferometric phase of said complex correlation, through the digital data processing module;
    - Resolution of the absolute and relative ambiguity of the interferometric phase, through the digital data processing module;
    - Obtaining a complete set of orbital elements and / or a state vector of the
    satellite from the interferometric phase and a differential correction technique, through the digital data processing module.
    In a preferred embodiment of the method for the determination of satellite orbits according to the invention, in which the system for the determination of satellite orbit comprises as many homodyne reception and / or heterodyne reception devices as antennas the receiver device disposes in such a that each antenna is in signal communication 35 with a homodyne reception and / or heterodyne reception device and, each
    8


    Homodyne reception and / or reception device heteredonia is in signal communication with the digital data processing module, and in the steps of the procedure of:
    - Homodyne reception that includes sub-steps:
    o Consistent demodulation, each of the signals received by the baseband antennas are coherently demodulated;
    o Obtaining the components in phase and quadrature, the components in phase and quadrature of each baseband signal are obtained; I
    Heterodine reception, which includes the following sub-steps:
    o Intermediate frequency translation, each of the signals received by the intermediate frequency antennas is transferred;
    o Consistent demodulation, each of the intermediate frequency signals is coherently demodulated;
    o Obtaining the components in phase and quadrature, the components in phase and quadrature of each baseband signal are obtained.
    - Digitization, each of the components in phase and quadrature obtained is digitized;
    - Filtering, digital signals are filtered in the working band in satellite baseband;
    - Obtaining the complex cross correlation, the complex cross correlation of at least two digital signals is obtained;
    - Obtaining the interferometric phase, the interferometric phase of said complex correlation is obtained;
    - Resolution of the absolute and relative ambiguity, the absolute and relative ambiguity of the interferometric phase is resolved;
    - Obtaining a complete set of orbital elements and / or a satellite status vector, a complete set of orbital elements and / or a satellite status vector is obtained from the interferometric phase and a differential correction technique.
    In another preferred embodiment of the method for the determination of satellite orbits according to the invention, in which the system for the determination of satellite orbits further comprises a signal combiner, said method comprises the following steps:
    9


    - Acquisition of the radio frequency signals emitted by the satellite by the reflector elements and sending said signals to the receiving device;
    - Reception by one of the antennas of the signal transmitted by a reflector element and by the other antenna of the signal transmitted by another reflector element or of the radio frequency signal emitted by the satellite;
    - Combination of the signals received by the antennas through the signal combiner;
    - Homodyne reception, through the homodyne reception device, which includes the following sub-steps:
    o Consistent demodulation of the combined baseband signal;
    o Obtaining the components in phase and quadrature of the baseband signal; I
    Heterodine reception, through the heterodyne reception device, which includes the following sub-steps:
    o Intermediate frequency translation of the combined signal;
    o Consistent demodulation of the signal at intermediate frequency to baseband;
    o Obtaining the components in phase and quadrature of the baseband signal.
    - Digitization of the components in phase and quadrature obtained;
    - Filtering of the digital signal in the working band in the satellite baseband;
    - Obtaining the complex autocorrelation of the digital signal filtered with this same digital signal filtered with different temporal displacements;
    - Obtaining the interferometric phase of said complex autocorrelation;
    - Resolution of the absolute and relative ambiguity of the interferometric phase;
    - Obtaining a complete set of orbital elements and / or a satellite status vector from the interferometric phase without absolute and relative ambiguity and a differential correction technique.
    As mentioned above, for the resolution of the absolute ambiguity of the interferometric phase, apart from the mentioned methods, there is the possibility of using a specific procedure. This method is based on using the interferometric phases obtained and an initial state vector of the arbitrary satellite.
    This procedure for resolving the absolute ambiguity of the interferometric phase comprises the following steps:
    10
    image7
    image8
    image9
    image10


    This digital data processing module (10) is configured so that once at least one interferometric phase has been obtained, it resolves the absolute and relative ambiguity of said interferometric phase and obtains a set of orbital elements and / or a status vector of the satellite from said interferometric phase without ambiguity and a differential correction technique.
    In this preferred embodiment, the homodyne reception devices (8) use the same reference clock preferably generated with a PLL in combination with a low frequency reference sinusoidal signal.
    A preferred embodiment of the procedure for the determination of satellite orbits configured to emit a radio frequency signal according to the invention, from the preferred embodiment of a system for the determination of satellite orbits comprising at least two reflecting elements (1) and a receiving device (2) according to that of Fig. 3, said method comprises the following steps:
    - Acquisition of radio frequency signals emitted by the satellite by the elements
    reflectors (1) and sending said signals to the receiving device (2);
    - Reception by one of the antennas (7) of the signal transmitted by a reflector element
    (1) and by the other two antennas (7) of the signals transmitted by the other reflector elements (1) or, reception by one of the antennas (7) of the signal transmitted by a reflector element (1) and by another of the two antennas (7) of the signal transmitted by another reflector element (1) and by the other of the two antennas (7) of the radio frequency signal emitted by the satellite.
    - Homodyne reception, through the homodyne reception device, which includes the following sub-steps:
    i. Consistent demodulation of each signal received by the baseband antennas;
    ii. Obtaining the components in phase and quadrature of each baseband signal; and / or -Digitalization of the components in phase and quadrature obtained, through the digital data processing module (10);
    - Filtration of each digital signal in the working band in the satellite baseband, through the digital data processing module (10);
    fifteen
    image11


    The digital data processing module (10) is configured to digitize the phase and quadrature component obtained by the coherent demodulator (8), filter it in the digital signal the working band in the satellite baseband and obtain at least one phase interferometric from the complex autocorrelation between the filtered digital signal and this filtered digital signal
    5 with different temporal displacements.
    This digital data processing module (10) is configured so that once at least one interferometric phase has been obtained, it resolves the absolute and relative ambiguity of said interferometric phase and obtains a set of orbital elements and / or a vector of
    10 state of the satellite from said interferometric phase without ambiguity and a differential correction technique.
    Fig. 5 shows a schematic view of an embodiment of the system for the determination of satellite orbits according to the invention comprising two elements
    15 reflectors (1) configured to receive the radio frequency signal emitted by the satellite and transmit it to a receiving device (2) that is configured to receive the signal transmitted by said reflector elements (1) as well as to receive the radio frequency signal broadcast by satellite.
    A preferred embodiment of the procedure for the determination of satellite orbits configured to emit a radio frequency signal according to the invention, from the preferred embodiment of a system for the determination of satellite orbits comprising at least two reflecting elements (1 ) and a receiving device (2) according to that of Fig. 4, said method comprises the following steps:
    25 -Acquisition of the radio frequency signals emitted by the satellite by the reflector elements (1) and sending said signals to the receiving device (2); -Reception by one of the antennas (7) of the signal transmitted by a reflector element
    (1) and by the other two antennas (7) of the signals transmitted by the other reflector elements (1) or, reception by one of the antennas (7) of the signal transmitted by
    30 a reflector element (1) and by another of the other two antennas (7) of the signal transmitted by another reflector element (1) and by the other of the other two antennas (7) of the radio frequency signal emitted by the satelite.
    -Combination of the signals received by the antennas (7); - Homodyne reception, through the homodyne reception device, which includes the following 35 sub-steps:
    • Consistent demodulation of the combined baseband signal;
    17
    image12
    权利要求:
    Claims (1)
    [1]
    image 1
    image2
    image3
    image4
    image5
    image6
    image7
    类似技术:
    公开号 | 公开日 | 专利标题
    US8570220B2|2013-10-29|Navigation receiver
    US11085990B2|2021-08-10|Angle of arrival measurements using RF carrier synchronization and phase alignment methods
    JP4861428B2|2012-01-25|Processing signal sample sequences
    JP2014139574A|2014-07-31|Multiphase code generator and gnss receiver
    JP6909023B2|2021-07-28|Radar device and radar method
    ES2692175A1|2018-11-30|SYSTEM AND PROCEDURE FOR THE DETERMINATION OF SATELLITE ORBITS |
    EP3533168B1|2020-09-23|Receiver and method for providing a phase coherency for frequency hopping multitone signals
    US10551162B2|2020-02-04|Code-modulated phased-array interferometric imaging
    Chauhan et al.2016|Code-modulated interferometric imaging system using phased arrays
    JP5933559B2|2016-06-15|Signal capturing apparatus and method
    US8810449B2|2014-08-19|Satellite radio receiver
    RU155152U1|2015-09-20|DEVICE FOR NAVIGATION-TEMPORARY DEFINITIONS BY SIGNALS OF GLOBAL NAVIGATION SATELLITE SYSTEMS
    JP2016531287A|2016-10-06|Improved receiver alias removal by adding an offset
    Park et al.2018|A design and implementation of software defined radio for rapid prototyping of GNSS receiver
    JP2012008012A|2012-01-12|Receiver
    Lázaro2012|Gnss array-based acquisition: Theory and implementation
    US20210033736A1|2021-02-04|Satellite positioning signal receiving device
    JP4735550B2|2011-07-27|Code correlation processing method in receiver of spread spectrum communication system
    WO2020260662A1|2020-12-30|Systems and methods for determining satellite orbit parameters
    Arribas Lázaro2012|GNSS array-based acquisition: theory and implementation
    EP3602130A1|2020-02-05|Methods and devices for page synchronization of a communication signal
    同族专利:
    公开号 | 公开日
    ES2692175B2|2019-03-25|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    WO2020260662A1|2019-06-28|2020-12-30|Asgard Space, S.L.|Systems and methods for determining satellite orbit parameters|
    法律状态:
    2018-11-30| BA2A| Patent application published|Ref document number: 2692175 Country of ref document: ES Kind code of ref document: A1 Effective date: 20181130 |
    2019-03-25| FG2A| Definitive protection|Ref document number: 2692175 Country of ref document: ES Kind code of ref document: B2 Effective date: 20190325 |
    优先权:
    申请号 | 申请日 | 专利标题
    ES201730749A|ES2692175B2|2017-05-31|2017-05-31|SYSTEM AND PROCEDURE FOR THE DETERMINATION OF SATELLITE ORBITS|ES201730749A| ES2692175B2|2017-05-31|2017-05-31|SYSTEM AND PROCEDURE FOR THE DETERMINATION OF SATELLITE ORBITS|
    [返回顶部]