• 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:
    Disclosed are a rotation missing plot tracking system and method for a double-reflection-surface satellite antenna, which are used for solving the deficiency of an existing satellite antenna automatic tracking system, characterized by comprising a main reflection surface, a secondary reflection surface and a feed source, wherein the main reflection surface is provided with a servo tracking unit and a main control unit; the main reflection surface, the secondary reflection surface and the feed source are coaxially arranged; one of the main reflection surface and the secondary reflection surface can rotate around an axial centre and is provided with a rotation mechanism; and the rotating main reflection surface or secondary reflection surface is eccentrically provided with a signal local-failure zone. Compared with stepped tracking, the present invention has a high precision and is quick in response; compared with conical scanning tracking, a main reflection surface and a secondary reflection surface are coaxially arranged, thereby decreasing a side lobe, reducing the interference of an adjacent satellite and improving the applicability; and compared with single-pulse tracking, by using a rotating and eccentrical signal local-failure zone, a quasi-sinusoidal signal of a model intensity period change can be acquired, which has a simple device and a low cost.
    公开号:ES2711662A2
    申请号:ES201990025
    申请日:2017-08-31
    公开日:2019-05-06
    发明作者:Changsong Qi；Hongjun Pan；Weiguo Zhuo；Haihua Yu
    申请人:Sinotrust Marine Zs Satellite Communication Co Ltd；
    IPC主号:
    专利说明:

    [0001]
    [0002] SYSTEM AND METHOD FOR TRACKING OF THE MISSING FRAME DURING TURNOVER
    [0003]
    [0004] Technical field
    [0005]
    [0006] The present invention relates to the field of communication by satellite, in particular to a system and method for tracking missing frames during the rotation of a dual-reflector satellite antenna.
    [0007]
    [0008] Background of the technique
    [0009]
    [0010] "Satcom in motion" is an abbreviated expression of "earth station communication system of moving satellite", which is used for communication between a mobile carrier and a satellite. Due to the weakness and strong directionality of satellite signals, it is required that the deviation between an antenna and a satellite should be detected in real time, and the position of the antenna should be adjusted at the moment, in particular, to ensure an alignment in time real between the antenna and the satellite, to convert a stable signal received by a mobile carrier (such as a ship, a train and the like) for communication. Therefore, as one of the main technologies for satellite antennas, the technology of automatic antenna tracking is essential for stable communication between a mobile carrier and a satellite. Currently, the commonly used automatic antenna tracking technologies include step tracking, conic exploration tracking, and monopulse tracking.
    [0011]
    [0012] Step tracking, also known as end tracking, is a method to determine if an antenna is aligned with a satellite according to the maximum value of a beacon signal per satellite: an azimuth plane or an inclination plane of an antenna It rotates slightly within a period of time, and the antenna adjusts by increasing or decreasing a signal level, so that the antenna is gradually aligned with a satellite. While step tracking has disadvantages that the antenna beam may not remain in the direction perfectly aligned with, but wobbles around, the satellite, leading to low tracking accuracy, slow response and intense satellite interferences.
    [0013]
    [0014] Tracing by conical scanning, by means of the continuous rotation of the beam around an antenna axis, obtains the signal of angular position error of the satellite mark that is bypassed of the antenna axis, and the error signal triggers a servo system to rotate the antenna in the direction in which the error can be reduced to track the satellite. The method of tracking by conical exploration has the disadvantages that a power source is diverted from the focal point of a reflector, or there is an included angle between a main tree of the antenna and the direction of a signal axis by satellite, with a a problem that never ceases from increasingly larger lateral lobes and intense satellite interferences, which limits the application of tracking by conical exploration in mass communication.
    [0015]
    [0016] Monopulse tracking is an advanced tracking method, which can obtain the full azimuth and inclination errors of an antenna beam that deviates from a satellite within a one-pulse interval, and can trigger a servo system to enable the antenna Align to the satellite quickly. Tracking by monopulses has the characteristics of high sensitivity and slight satellite interference, but being large and complex in a power supply system for it, with high technical requirements and expensive equipment, limited in high level fields and military, unlikely that become popular.
    [0017]
    [0018] Summary of the invention
    [0019]
    [0020] Technical solutions
    [0021]
    [0022] To eliminate the defects of the existing automatic satellite antenna tracking system, the invention provides a system and method for tracking missing frames during the rotation of a dual reflector satellite antenna, with high precision, low satellite interferences and low costs.
    [0023]
    [0024] The technical solution adopted by the invention is as follows: a system for tracking missing frames during the rotation of a dual-reflector satellite antenna, comprising a primary reflector, a secondary reflector and a power source, in which the primary reflector is provided with a servo tracking unit and a main control unit; the primary reflector and the secondary reflector are arranged coaxially with the power supply, one of the primary reflector and the secondary reflector can rotate around the axis and is provided with a turning mechanism, and an area in which the signals partially fail is available eccentrically on the rotating primary reflector or the secondary reflector.
    [0025]
    [0026] The turning mechanism rotates at a constant speed.
    [0027]
    [0028] The area in which signals fail partially is disposed in the secondary reflector.
    [0029] The area in which signals fail partially is arranged in a position of the maximum field density in the secondary reflector.
    [0030]
    [0031] The area in which signals fail partially is disposed in the primary reflector.
    [0032]
    [0033] The area in which the signals fail partially is arranged on an edge in the primary reflector.
    [0034]
    [0035] An automatic tracking method used by the system to track missing frames during the rotation of a dual reflector satellite antenna, comprising the steps as follows: a) when the axis of a primary reflector is deflected from a satellite, the primary reflector groups satellite microwave signals to a secondary reflector and reflects satellite microwave signals to a power source, and signals are generated with periodic intensity fluctuation due to the rotation of an area in which the signals partially fail; b) the main control unit receives and processes the signals, calculates the direction of deviation of the primary reflector of the satellite according to the distribution of signal strength, and calculates the degree of deviation of the primary reflector of the satellite according to the deviation of extreme value of the signal intensity; c) the main control unit operates the servo tracking unit to enable the primary reflector to move towards the satellite; and d) when the axis of the primary reflector is aligned with the satellite, the signal intensity obtained by the power supply maintains the same when the area in which the signals fail partially rotates, and the main control unit maintains the state of the signal. Servo tracking unit without changes.
    [0036]
    [0037] Advantageous effects
    [0038]
    [0039] In comparison with step tracking, the invention has the advantages of high precision and fast response; in comparison with scanning by conical exploration, the primary reflector and the secondary reflector are arranged coaxially, therefore the lateral lobes are reduced, the satellite interference is alleviated and the applicability is improved; and in comparison with monopulse tracking, sinusoidal signals can be obtained with periodic intensity fluctuation using a rotating and eccentric area in which the signals partially fail, simple in structure and low in costs.
    [0040]
    [0041] Brief description of the drawings
    [0042]
    [0043] Figure 1 is a schematic diagram of the first embodiment of the present invention when it is directed towards a satellite.
    [0044] Figure 2 is a schematic diagram of an area in which the signals partially fail according to the first embodiment of the present invention.
    [0045]
    [0046] Figure 3 is a schematic diagram showing the field density of a secondary reflector when it is directed towards a satellite according to the first embodiment of the present invention.
    [0047]
    [0048] Figure 4 is a schematic diagram of a secondary reflector in a first position when deviating from a satellite according to the first embodiment of the present invention.
    [0049]
    [0050] Figure 5 is a schematic diagram showing the field density of a secondary reflector in a first position according to the first embodiment of the present invention.
    [0051]
    [0052] Figure 6 is a schematic diagram showing a secondary reflector in a second position when deviating from a satellite according to the first embodiment of the present invention.
    [0053]
    [0054] Figure 7 is a schematic diagram showing the field density of the secondary reflector in the second position according to the first embodiment of the present invention.
    [0055]
    [0056] Figure 8 is a curve of signals received by a power source according to the first embodiment of the present invention.
    [0057]
    [0058] Figure 9 is a schematic block diagram of the principle of the first embodiment of the present invention.
    [0059]
    [0060] Figure 10 is a schematic diagram of the second embodiment of the present invention when it is directed towards a satellite.
    [0061]
    [0062] Figure 11 is a schematic diagram of an area in which the signals partially fail according to the second embodiment of the present invention.
    [0063]
    [0064] primary reflector 1, secondary reflector 2, power supply 3, rotation mechanism 4 and area in which the signals partially fail 5.
    [0065]
    [0066] Detailed description of the invention
    [0067] The invention will now be further described, taking a ring focus antenna as an example, with reference to the accompanying drawings.
    [0068]
    [0069] In the first embodiment, as shown in Figures 1 and 2, an automatic tracking system for a ring focus antenna comprises a primary reflector 1, a secondary reflector 2 and a power source 3, in which the primary reflector 1 is provided with a servo tracking unit and a main control unit; the primary reflector 1, the secondary reflector 2 and the power supply 3 are arranged coaxially, the secondary reflector 2 can rotate about the axis and is provided with a turning mechanism 4, and an area in which the signals partially fail 5 disposes eccentrically in a position of the maximum field density in the secondary reflector 2.
    [0070]
    [0071] In the first embodiment, the area in which the signals partially fail 5 can be implemented by local defect, signal absorbing coating, etc.
    [0072]
    [0073] In the first embodiment, as shown in Figure 1, when the axis of the primary reflector 1 is aligned with the satellite, the primary reflector 1 groups microwave signals to the secondary reflector 2 in which the field intensity distribution is not uniform , the microwaved field strength being closer to the edge of the denser primary reflector 1, that is, the field strength closest to the center of the secondary reflector 2 is denser, as shown in Figure 3. At this time , the secondary reflector 2 rotates one revolution, the microwave signal energy lost in the area in which the signals partially fail 5 maintains the same along the circumference of rotation, that is, the power supply 3 receives stable signals .
    [0074]
    [0075] In the first embodiment, as shown in Figures 4 and 6, when the axis of the primary reflector 1 deviates from the satellite and the secondary reflector 2 is in the first and second positions respectively, the field density distribution in the secondary reflector 2 is shown in Figures 5 and 7 respectively. At this time, the secondary reflector 2 rotates one revolution, the microwave signal energy lost in the area in which the signals partially fail 5 changes along the circumference of rotation, the power supply 3 can actually receive signal with periodic intensity fluctuation, and the signal waveform refers to the position, shape and speed of rotation of the area in which the signals partially fail 5. When the technical parameters are properly adjusted, the signal intensity will appear as a wave sinusoidal as shown in Figure 8.
    [0076]
    [0077] The automatic tracking method used by the automatic antenna tracking system of Ring focus in the first realization comprises the steps as indicated below: a) When the axis of a primary reflector 1 is deviated from a satellite, the primary reflector 1 groups satellite microwave signals to a secondary reflector 1 and reflects the satellite microwave signals to a power source 3, and signals are generated with periodic intensity fluctuation due to the rotation of an area in which the signals partially fail 5; b) the main control unit receives and processes the signals, calculates the direction of deviation of the primary reflector 1 of the satellite according to the distribution of intensity of the signals, and calculates the degree of deviation of the primary reflector 1 of the satellite in accordance with the deviation of the extreme value of the signal intensity; c) the main control unit operates the servo tracking unit to enable the primary reflector 1 to move towards the satellite; and d) when the axis of the primary reflector 1 is aligned with the satellite, the signal intensity obtained by the power source 3 maintains the same when the area in which the signals partially fail 5 rotates, and the main control unit maintains the status of the servo tracking unit without changes. In comparison with step tracking, the invention has the advantages of high precision and fast response; in comparison with scanning by conical exploration, the primary reflector 1 and the secondary reflector 2 are arranged coaxially, therefore the lateral lobes are reduced, the satellite interference is alleviated and the applicability is improved; and in comparison with monopulse tracking, sinusoidal signals with periodic intensity fluctuation can be obtained by using a rotating and eccentric area in which the signals partially fail 5, simple in structure and low in costs.
    [0078]
    [0079] In the first embodiment, as shown in Figures 1 and 2, an area is provided in which the signals partially fail 5 near a position of the maximum field strength density in the secondary reflector 2. The secondary reflector 2 has a small size and a good design that can guarantee a fast and stable turn, in particular, a faster tracking speed and a higher tracking accuracy are made, and when the speed of rotation is fast enough, the first realization can look like or even outperform in technical performance compared to monopulse tracking; the area in which the signals partially fail 5 is provided with an area with higher field density, so that the tracking speed and the tracking accuracy can be further improved.
    [0080]
    [0081] In the second embodiment, as shown in Figures 10 and 11, the primary reflector 1 rotates, and the area in which the signals partially fail 5 is disposed at the edge of the primary reflector 1, with a similar principle behind, in both cases, to use the rotation of a reflector with an area in which the signals partially fail 5 eccentric to obtain signals with periodic fluctuation of intensity, enabling an automatic tracking of the antenna by satellite on such basis.
    [0082]
    [0083] It should be appreciated that the above described embodiments of the present invention are merely illustrative and are not intended to limit the embodiments of the present invention. It will be apparent to those skilled in the art that various other changes and modifications can be made based on the above description. All the realizations do not need to be or can not be exclusive. And such obvious variations and modifications pertaining to the true spirit of the invention remain within the scope of the invention.
    权利要求:
    Claims (7)
    [1]
    A system for tracking missing frames during the rotation of a dual-reflector satellite antenna, comprising a primary reflector (1), a secondary reflector (2) and a power supply (3), providing the primary reflector (1) ) with a servo tracking unit and a main control unit, in which the primary reflector (1) and the secondary reflector (2) are arranged coaxially with the power supply (3), one of the primary reflector (1) and the secondary reflector (2) can rotate about the axis and is provided with a turning mechanism (4), and an area in which the signals partially fail (5) is arranged eccentrically on the primary rotating reflector (1) or secondary reflector (two).
    [2]
    2. The system for tracking missing frames during rotation of a dual reflector satellite antenna according to claim 1, wherein the turning mechanism (4) rotates at a constant speed.
    [3]
    3. The system for tracking missing frames during the rotation of a dual reflector satellite antenna according to claim 1 or 2, wherein the area in which the signals partially fail (5) is provided in the secondary reflector ( two).
    [4]
    4. The system for tracking missing frames during the rotation of a dual reflector satellite antenna according to claim 3, wherein the area in which the signals partially fail (5) is provided in a position of a density of maximum field in the secondary reflector (2).
    [5]
    5. The system for tracking missing frames during the rotation of a dual reflector satellite antenna according to claim 1 or 2, wherein the area in which the signals partially fail (5) is provided in the primary reflector ( one).
    [6]
    6. The system for tracking missing frames during the rotation of a dual reflector satellite antenna according to claim 5, wherein the area in which the signals partially fail (5) is provided at an edge in the primary reflector (one).
    [7]
    7. An automatic tracking method used by the system to track missing frames during the rotation of a dual reflector satellite antenna according to claim 1, comprising the steps as indicated below:
    a) when an axis of a primary reflector (1) is deviated from a satellite, the primary reflector (1) groups signals from satellite microwaves to a secondary reflector (2) and reflects satellite microwave signals to a power supply (3), and signals are generated with periodic intensity fluctuation due to the rotation of an area in which the signals partially fail (5);
    b) a main control unit receives and processes the signals, calculates the direction of deviation of the primary reflector (1) of the satellite according to signal intensity distribution, and calculates a degree of deviation of the primary reflector (1) of the satellite according to extreme value deviation of signal intensity;
    c) the main control unit operates a servo tracking unit to move the primary reflector (1) towards the satellite; Y
    d) when the axis of the primary reflector (1) is aligned with the satellite, the signal intensity obtained by the power source (3) maintains the same when the area in which the signals partially fail (5) rotates, and the Main control unit maintains a state of the servo tracking unit without changes.
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    引用文献:
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    DE29724409U1|1997-10-14|2001-11-15|Rr Elektronische Geraete Gmbh|Tracking system for aligning a swiveling reflective antenna|
    WO2010080545A2|2008-12-17|2010-07-15|Asc Signal Corporation|Subreflector tracking method, apparatus and system for reflector antenna|
    CN203242736U|2013-05-21|2013-10-16|深圳市华信天线技术有限公司|Satellite antenna device|
    CN103715508A|2013-12-31|2014-04-09|深圳市华信天线技术有限公司|Method and device for automatically tracking satellite through satellite antenna|
    CN106299699B|2016-09-19|2017-07-21|中信海洋（舟山）卫星通信有限公司|A kind of double-reflecting face satellite antenna rotary missing plot tracking system and method|
    CN206003969U|2016-09-19|2017-03-08|中信海洋（舟山）卫星通信有限公司|A kind of double-reflecting face satellite antenna rotary missing plot tracking system|CN106299699B|2016-09-19|2017-07-21|中信海洋（舟山）卫星通信有限公司|A kind of double-reflecting face satellite antenna rotary missing plot tracking system and method|
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    RU2665495C1|2017-10-11|2018-08-30|Российская Федерация, от имени которой выступает Государственная корпорация по космической деятельности "РОСКОСМОС"|Dual-mirror antennas with mechanical targeting|
    CN113258284B|2021-06-10|2021-11-23|中国人民解放军海军工程大学|High-power microwave ring-focus dual-reflector antenna|
    法律状态:
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    CN201610828474.4A|CN106299699B|2016-09-19|2016-09-19|A kind of double-reflecting face satellite antenna rotary missing plot tracking system and method|
    PCT/CN2017/099839|WO2018049986A1|2016-09-19|2017-08-31|Rotation missing plot tracking system and method for double-reflection-surface satellite antenna|
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