CN111948464A - Bias-feed wireless closed-loop self-tracking phase correction system - Google Patents
Bias-feed wireless closed-loop self-tracking phase correction system Download PDFInfo
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Abstract
The invention discloses an offset-feed wireless closed-loop self-tracking phase correction system, and aims to provide a system which is not influenced by an external weather environment and can quickly and accurately detect the relative phase and relative gain change of a tracking sum-difference link and a tracking difference link. The invention is realized by the following technical scheme: a radio frequency signal generator configured by a space flight measurement and control system and a satellite application system outputs a radio frequency signal, the radio frequency signal is radiated to an auxiliary reflecting surface through a bias-feed horn antenna positioned in a main reflecting surface, the radio frequency signal sequentially enters a feed source network, a low-noise amplifier and a down converter on a tracking sum-difference link, and then enters a tracking baseband processor unit to perform bias-feed wireless closed-loop phase correction to obtain a relative phase and a sensitivity coefficient under the condition of bias-feed wireless closed-loop phase correction, under the condition that the relation between the relative phase and the sensitivity coefficient of the original bias-feed wireless closed-loop phase correction and the satellite phase correction is known, the calculated relative phase and the sensitivity coefficient are placed into a tracking baseband, and satellite phase correction-free tracking is realized based on the bias.
Description
Technical Field
The invention relates to an offset-feed wireless closed-loop self-tracking phase correction system for S, C, X frequency band satellite phase correction-free tracking, which is mainly applied to the fields of aerospace measurement and control, satellite application and the like.
Background
With the rapid development of the aerospace industry, the number of spacecrafts such as on-orbit satellites and the like is continuously increased, the long pipe task of ground measurement and control equipment becomes increasingly heavy, and in the fields of aerospace measurement and control, satellite application and the like, the cross-coupling index of a system is continuously deteriorated due to the influence of multiple factors such as zero drift of an antenna electric axis, equipment combination change, environmental temperature change, system equipment maintenance and replacement and the like, so that the tracking performance of the antenna is reduced. In order to realize real-time tracking of a satellite, a space flight measurement and control system and a satellite application system need to frequently calibrate relative phase and gain changes of a device tracking sum and difference link, so that a quick, simple and reliable phase calibration method is needed. With the increasing working frequency range, the aerospace measurement and control and satellite application is gradually expanded from the S frequency range and the C frequency range to the X frequency range. With the improvement of the working frequency band, the requirements on the distance and the height of a calibration tower in the traditional tower calibration phase calibration mode are higher and higher. The distance between the calibration tower and the satellite measurement and control and receiving antenna needs to meet the far field condition according to the far field formula 2D2And lambda, the distance between the calibration tower and the antenna under the X frequency band for the traditional 12-meter caliber antenna can be calculated to be 11.5 kilometers. The antenna can be calibrated at the lowest elevation angle of 3 degrees, and the height of a calibration tower is 600 meters. Therefore, no matter the selection is from the field or the cost is considered, the calibration tower meeting the far-field calibration condition cannot be built.
Due to the limitation on the calibration conditions of the tower, in recent years, satellite calibration methods, radio satellite calibration methods and other tower-less calibration methods are successively developed for aerospace measurement and control systems and satellite application systems adopting a dual-channel single-pulse angle tracking system. The calibration of the radio frequency stars needs to be added with high-precision calibration equipment, and the radio frequency star flow is limited, so that the calibration tower can only be suitable for a deep space measurement and control system with high gain and low system noise temperature, and most sites are still difficult to build to meet the calibration conditions of the near-earth calibration phase in an X frequency band. And a calibration tower still needs to be built for near-earth phase calibration, the cost is high, and the phase calibration precision is reduced. Radio star school looks, near ground school looks and to the star school looks all are susceptible to rainfall and strong wind weather, and the rainfall influences the intensity of received signal, and the gust can cause the directional swing of antenna, and two kinds of weather conditions all can cause the school to take turns the result out of tolerance or school to take turns to and fail. Therefore, most of the existing measurement and control systems and satellite application systems without calibration towers mostly adopt satellite calibration phase calibration to calibrate the satellite, but the satellite calibration phase is limited by various factors such as central plan, data transmission data issuing time, orbit height and the like, meanwhile, a polarization antenna is needed for the satellite calibration phase, the possibility that the antenna deflects to generate a main beam exists in the polarization process, and data receiving is interrupted at the moment, so that the measurement and control systems and the satellite application systems can be used for calibrating the satellite phase with fewer circles. Once the equipment combination is changed, the environmental temperature changes greatly or the modules are replaced due to the maintenance of the tracking link, the original phase calibration data cannot be used, and when the circle task does not meet the satellite phase calibration condition, the circle task cannot be executed.
The bias-feed wireless closed-loop phase calibration is a process for simulating satellite phase calibration or tower phase calibration by using a system self-closed-loop link, the relative phase and sensitivity coefficient of a tracking sum and difference link under the condition of the bias-feed wireless closed-loop phase calibration are different from the results of satellite phase calibration or tower phase calibration, but the relative phase under two phase calibration modes has a relatively fixed relation, and the sensitivity coefficient also has a relatively fixed relation. Subsequently, when the original satellite phase calibration data is unavailable due to the fact that equipment combination is changed, the environment temperature is greatly changed or system equipment is maintained and replaced and the like, the current real relative phase and sensitivity coefficient of the system can be calculated through the bias-feed wireless closed-loop phase calibration monitoring tracking and the relative phase and sensitivity coefficient change of the difference link. The fixed relation of the relative phase and the fixed relation of the sensitivity coefficient under the bias-feed wireless closed loop and satellite phase correction modes can obtain specific data by comparing the phase correction results of the two phase correction methods after the aerospace measurement and control or satellite application system installation joint test is finished.
The phase calibration has two purposes, the first is to measure the relative phase of the whole tracking sum and difference link including the feed network and the downlink tracking channel, the relative phase of the tracking sum and difference link is counteracted by adjusting the phase shift values of the azimuth phase shifter and the pitching phase shifter in the tracking baseband to avoid cross coupling, the second is to adjust the sensitivity coefficient of the tracking baseband according to the appointed orientation sensitivity to make the antenna deviate from a certain angle, the actual output angle difference voltage of the tracking baseband is consistent with the calculated angle error voltage according to the orientation sensitivity, and the change of the sensitivity coefficient is mainly related to the relative gain change of the tracking sum and difference link. The phase adjustment between the sum and difference channels, commonly referred to as phase correction, is critical for tracking, and if the phase adjustment is not balanced, the tracking loop cannot track stably, or even at all. The phase difference between the channels varies with the operating frequency, the polarization mode and the equipment combination, so that each state must be specially adjusted.
The first purpose of phase correction is to adjust the theta values in tracking the two phase shifters azimuth and pitch in baseband by a step-and-search method
Is marked as theta1. If it is not
Cross coupling can occur, namely, when the azimuth is biased, the pitching is carried out at the same time, and when the pitching is biased, the azimuth is also carried out at the same time, so that the circling phenomenon occurs in the tracking process, and the target can be lost when the target is serious. The corrected phase fluctuates with temperature, device aging and other factors, which causes the fluctuation of the sum channel phase and the difference channel phase, and the unstable amount of the sum channel after phase correction also causes the fluctuation of the sum channel phase and the difference channel phase. Due to the phase disparity of the sum and difference channels, there is a crossed signal component, which is referred to as cross-coupling. Because the feeder network and the downlink tracking channel in the antenna center body are outdoor equipment, the change of outdoor temperature can cause the change of the electrical characteristics of the device, and the influence on the transmission phase of the device is large. The larger the temperature change, the larger the phase change, and the more significant the cross-coupling degradation. That is, the presence of a relative phase difference before the sum and difference signals are combined causes cross-coupling in the azimuth and pitch error voltages, and the greater the relative phase difference, the greater the cross-coupling, and also causes a reduction in the angular error sensitivity. In addition, when the operating frequency point of the tracking receiver and the polarization of the antenna are changed, the output of the angular error detector may be changed due to the change of the front-end phaseIf the cross coupling is not removed by a phase shifter in a post-synthesis link, the tracking receiver will be mutually coupled when outputting azimuth and pitch error voltages, namely, after the azimuth or pitch deviates from the zero point of the antenna, the tracking receiver generates voltages which cannot be generated in the pitch or azimuth, so that the tracking receiver outputs angular error information with larger error, and the antenna cannot normally track a target in serious conditions, and the azimuth and pitch error voltages are compared with a cross coupling coefficient, so that the influence of the coefficient on the tracking stability is larger.
The directional sensitivity of the system is determined by the servo capability of the antenna and is a certain value, which is recorded as KV/mil (i.e., K volts/mil). The second purpose of phase correction is to find the relative phase θ1Post-adjustment k value, denoted as k1When the antenna deviates from a dense angle, the angular error of the tracking baseband output is just KV. If k is1The calculation is not accurate, the small angle error voltage output by the tracking baseband is too low to cause insufficient servo drive capability and cause high elevation angle dynamic lag of the antenna, and the large angle error voltage output by the tracking baseband causes overlarge servo drive and causes tracking oscillation of the antenna. It can be seen that the accuracy of the phase correction result is crucial to the tracking performance of the system.
Disclosure of Invention
The invention aims to provide an offset-feed wireless closed-loop self-tracking phase correction system which is not influenced by the external weather environment, has multiple adaptive frequency bands and can quickly and accurately detect the relative phase and relative gain change of a tracking sum link and a tracking difference link, aiming at overcoming the problems that the former phase correction data of the system is invalid and the system cannot execute tasks when the satellite phase correction is limited due to the change of equipment combination, the large change of the environmental temperature or the replacement of a module and the like.
The above object of the present invention can be achieved by an offset-fed wireless closed-loop self-tracking phase correction system, comprising: the self-matched radio frequency signal generator of the space flight measurement and control system and the satellite application system, the parabolic antenna used by the space flight measurement and control system and the satellite application system, the offset feed horn antenna installed in the main reflecting surface of the parabolic antenna, the feed network positioned in the main reflecting surface of the antenna and the central body of the antenna, the low noise amplifier and the down converter in the central body, the equal-length phase-stable cables L1 and L2 from the central body of the antenna to the tower base of the antenna, and the tracking base band positioned at the tower base of the antenna, and is characterized in that: the radio frequency signal output by the radio frequency signal generator positioned at the antenna tower base is transmitted to the offset feed horn antenna arranged in the main reflecting surface of the parabolic antenna through the long cable, the radio frequency signal radiated by the offset feed horn antenna is reflected by the auxiliary reflecting surface of the parabolic antenna and then sequentially enters the feed network, tracking sum and difference signals are formed in the feed network, the sum and difference signals reach the antenna central body, are amplified by a low noise amplifier LNA1 and a low noise amplifier LNA2 which are respectively connected in series on a sum link and a difference link in the antenna central body, and are down-converted and amplified by a down converter D/C1 and a down converter D/C2 on the sum link and the difference link, then sent to a tracking baseband processing unit positioned below the antenna tower base through two equal-length intermediate frequency phase-stabilizing cables L1 and L2, thereby forming a dual-channel self-tracking offset feed wireless closed-loop self-tracking phase correction system connected between the feed network and the tracking baseband processing unit. The bias-feed wireless closed-loop self-tracking phase correction system is used for monitoring the relative phase and relative gain change of the tracking sum-difference link, the relative phase theta and the sensitivity coefficient k of the tracking sum-difference link of the space measurement and control system or the satellite application system are calculated under the condition that the satellite is not corrected, and the calculated relative phase theta and the sensitivity coefficient k of the tracking sum-difference link are arranged in the tracking baseband processing unit, so that the correction-free phase tracking of the satellite in the S, C, X frequency band is realized.
Compared with the prior art, the invention has the following beneficial effects.
The invention has low cost without adding extra equipment, and aims at the space measurement and control and satellite application system adopting the traditional parabolic antenna, and measures the relative phase theta of the system by using the satellite phase calibration1Sensitivity coefficient k1Then, under the condition of unchanging equipment combination, the radio frequency signal output by the radio frequency signal generator of the system configuration is utilized to pass through the long circuitThe cable is sent to a bias feed horn antenna arranged in a main reflecting surface of the antenna, and radio frequency signals are reflected by an auxiliary reflecting surface and then sequentially enter a feed network, a low noise amplifier of a tracking sum-difference link, a down converter and then enter a tracking baseband of an antenna tower footing through equal-length phase-stabilizing cables. A radio frequency signal is output by a radio frequency signal generator configured by a space measurement and control system and a satellite application system, the radio frequency signal is sent to an input port of a bias feed antenna arranged in a main reflecting surface of the antenna, a main beam is aligned to a subsidiary reflecting surface of the antenna, the radio frequency signal output by the bias feed antenna enters a feed network after being reflected by the subsidiary reflecting surface, tracking sum-path and difference-path signals are formed in the feed network, and satellite calibration phase tracking is realized by bias feed wireless closed loop calibration. No additional equipment is required. The calibration of the phase without the ground still needs to be built into a costly calibration tower and the calibration of the radio star needs to be added with high-precision calibration equipment.
The invention is not influenced by the external weather environment, the radio frequency signal output by the radio frequency signal generator configured by the space measurement and control system and the satellite application system is sent to the input port of the offset feed horn antenna arranged in the main reflecting surface of the parabolic antenna through the long cable, the radio frequency signal radiated by the offset feed horn antenna is reflected by the auxiliary reflecting surface of the parabolic antenna and then sequentially enters the feed network, a tracking sum path and a difference path signal are formed in the feed network, the sum signal and the difference signal respectively enter and are differentially received to reach the antenna central body, the sum signal and the difference signal are respectively amplified by the low noise amplifier LNA1 and the low noise amplifier LNA2 which are respectively connected in series on the antenna central body and the difference link, the down conversion and the amplification are carried out through the down converter D/C1 and the down converter D/C2, and then the radio frequency signal is sent to the tracking baseband processing unit positioned below the, and forming an offset feed wireless closed loop connected between the feed network and the tracking baseband processing unit. The method is not influenced by external weather such as rain, strong wind and the like, does not need antenna matching, and can accurately monitor the relative phase and sensitivity coefficient change of the offset-fed wireless closed-loop calibration relative system at any time and under various weather conditions. The method can overcome the problems that the radio satellite phase correction, the near-earth phase correction and the satellite-to-satellite phase correction are easily influenced by rainfall and strong wind weather, the rainfall influences the intensity of received signals, and gusts cause antenna directional swing, so that the phase correction result is out of tolerance or the phase correction fails.
The adaptive frequency band is multiple. The invention obtains the relative phase theta through the bias-feed wireless closed-loop phase correction2' and coefficient of sensitivity k2', the true relative phase θ2Coefficient of sensitivity k2Calculating the true relative phase theta of the current sum and difference link based on the bias-fed wireless closed loop2＝θ1+θ2′-θ1', coefficient of sensitivity k2＝k1*k2′/k1', will theta2And k2The tracking baseband is arranged to complete the satellite tracking task, the satellite calibration-free tracking based on the offset-feed wireless closed loop is achieved, the satellite calibration-free tracking system can adapt to S frequency band, C frequency band and X frequency band, the problem that the radio satellite calibration is limited by the radio satellite flow is solved, and the phase calibration condition is difficult to meet at the X frequency band flow. Through practical tests and satellite tracking verification, the result obtained by the method is used for satellite tracking, the cross coupling is less than 1/7 in the S frequency band, and the cross coupling is less than 1/6 in the C frequency band and the X frequency band, so that the requirement that the cross coupling of the system satellite tracking is less than 1/3 can be met.
The invention monitors the change of the relative phase and the sensitivity coefficient of the system by using the bias-feed wireless closed-loop phase correction. When the states of the space measurement and control and satellite application system change, the satellite phase calibration method is not limited by the condition of satellite phase calibration, and the current relative phase and the sensitivity earth coefficient are calculated through the result of bias-feed wireless closed-loop phase calibration, so that the satellite tracking method can be used for satellite tracking. The method can be suitable for a plurality of frequency bands, the suitable frequency bands comprise an S frequency band, a C frequency band and an X frequency band which are commonly used by aerospace measurement and control and satellite application systems, and the relative phase and the sensitivity coefficient of the tracking link of the system of the three frequency bands can be effectively monitored by the method. The method is suitable for most ground station equipment of the aerospace measurement and control and satellite application system at present.
Drawings
FIG. 1 is a schematic block diagram of an offset-fed wireless closed-loop self-tracking phase correction system of the present invention.
Detailed Description
See fig. 1. In a preferred embodiment described below, an offset-fed wireless closed-loop self-tracking phase correction system comprises: the self-matched radio frequency signal generator of the space flight measurement and control system and the satellite application system, the parabolic antenna used by the space flight measurement and control system and the satellite application system, the offset feed horn antenna installed in the main reflecting surface of the parabolic antenna, the feed network positioned in the main reflecting surface of the antenna and the central body of the antenna, the low noise amplifier and the down converter in the central body, the equal-length phase-stable cables L1 and L2 from the central body of the antenna to the tower base of the antenna, and the tracking base band positioned at the tower base of the antenna, and is characterized in that: the radio frequency signal output by the radio frequency signal generator positioned at the antenna tower base is transmitted to the offset feed horn antenna arranged in the main reflecting surface of the parabolic antenna through the long cable, the radio frequency signal radiated by the offset feed horn antenna is reflected by the auxiliary reflecting surface of the parabolic antenna and then sequentially enters the feed network, tracking sum and difference signals are formed in the feed network, the sum and difference signals reach the antenna central body, are amplified by a low noise amplifier LNA1 and a low noise amplifier LNA2 which are respectively connected in series on a sum link and a difference link in the antenna central body, and are down-converted and amplified by a down converter D/C1 and a down converter D/C2 on the sum link and the difference link, then sent to a tracking baseband processing unit positioned below the antenna tower base through two equal-length intermediate frequency phase-stabilizing cables L1 and L2, thereby forming a dual-channel self-tracking offset feed wireless closed-loop self-tracking phase correction system connected between the feed network and the tracking baseband processing unit. The bias-feed wireless closed-loop self-tracking phase correction system is used for monitoring the relative phase and relative gain change of the tracking sum-difference link, the relative phase theta and the sensitivity coefficient k of the tracking sum-difference link of the space measurement and control system or the satellite application system are calculated under the condition that the satellite is not corrected, and the calculated relative phase theta and the sensitivity coefficient k of the tracking sum-difference link are arranged in the tracking baseband processing unit, so that the correction-free phase tracking of the satellite in the S, C, X frequency band is realized.
The tracking baseband processing unit includes: a sum-link automatic gain control circuit AGC connected with the D/C of the sum-link down converter and a carrier synchronization unit connected in series, a difference-link Automatic Gain Control (AGC) circuit connected with the D/C of the difference-link down converter, two coherent detectors connected after the difference-link Automatic Gain Control (AGC) and respectively connected with the two coherent detectors and the carrier synchronization unit on the azimuth branch and the pitch branchAn azimuth phaser and a pitch phaser connected. The carrier synchronization unit respectively controls the gains of the sum and difference links by using the control voltage output by the AGC control circuit on the sum link, and adjusts the position reference signal k after the AGC gain adjustment0cos(wt+θ0) Sending the difference signal u delta (t) of the azimuth phase discriminator to perform phase discrimination, and adjusting the pitching reference signal k after AGC gain adjustment0sin(wt+θ0) Sending the signal to a pitching phase discriminator to perform phase discrimination with a difference signal u delta (t), and performing low-pass filtering on the azimuth signal subjected to phase discrimination by a filter connected in series to remove high-frequency components to obtain an azimuth error voltage signal
The pitch angle error voltage signal of the phase-discriminated pitch signal after high-frequency components are removed through low-pass filtering of the pitch signal by the series-connected filter
Wherein k is0The sensitivity coefficient of the built-in tracking baseband during initial phase correction is shown, theta represents the phase shift values of the azimuth phase shifter and the pitch phase shifter,
is the relative phase of the sum and difference links. When correcting phase, the tracking baseband processing unit firstly finds out the phase value theta of the azimuth phase shifter by step-by-step adjustment
The angular error voltage output by the azimuth branch is maximized, and then the sensitivity coefficient K is determined according to the directional sensitivityAZAdjusting the maximum azimuth angle error voltage Ua to a predetermined value, and then finding out the phase value theta of the pitch phase shifter by adjusting the phase value theta step by step
The angular error voltage output by the pitching branch is maximized, and then the sensitivity coefficient K is determined according to the directional sensitivityE1And adjusting the maximum pitching angle error voltage Ue to a given value.
Space surveyTracking difference (delta) link signals in azimuth while phase correction by the control system
Tracking the signal of a difference (delta) link in pitch
For the relative phase of the sum and difference link, the sigma (sum) link signals are tracked: u ∑ (t) ═ cos (wt), tracking Δ (difference) link signals:
plus or minus when the left-handed signal is positive, plus or minus when the right-handed signal is negative, wherein: u ∑ (t) is a function of the sum signal over time, u Δ (t) is a function of the difference signal over time, a is the magnitude of the difference signal in azimuth, E is the magnitude of the difference signal in pitch, w is the angular frequency, w ═ 2 π f, f is the frequency of the tracking baseband ingress intermediate frequency and the difference signal.
The offset feed horn antenna is arranged at the position, in the main reflecting surface of the parabolic antenna, away from the radius of the outer edge 1/3 of the main reflecting surface, the influence of multipath interference on offset feed wireless closed loop phase correction is minimum, and the values of theta '-theta and k'/k are stable. Because the intermediate frequency of the tracking sum-difference link at the inlet of the tracking baseband processing unit has signals, the simulation is equivalent to the condition that an antenna deviates from a target by an angle in the process of satellite phase correction or tower phase correction, and at the moment, the tracking baseband processing unit corrects the phase to obtain the relative phase theta of the tracking sum-difference link under the condition of offset-feed wireless closed loop1' and coefficient of sensitivity k1′，θ1′≠θ1And k is1′≠k1，θ1And k1The relative phase and sensitivity coefficient of the tracking and difference links under the condition of phase calibration to the satellite are respectively. After the relative phase and the sensitivity coefficient of the tracking sum-difference link are changed, the tracking baseband processing unit monitors the relative phase and the relative gain change of the tracking sum-difference link based on the bias-feed wireless closed loop to obtain the relative phase and the relative gain change of the tracking sum-difference link under the condition of the bias-feed wireless closed loopRelative phase theta2' and coefficient of sensitivity k2' the relative phase theta of the system tracking sum and difference links at that time is deduced2＝θ1+(θ2′-θ1') and sensitivity coefficient k2＝k1*k2′/k1', at θ1、θ1′、θ2′、k1、k1′、k2' in the known case, the relative phase θ of the sum and difference links will be tracked2And coefficient of sensitivity k2The tracking baseband is arranged to be used for the satellite tracking task, so that the satellite phase correction-free tracking is realized based on the bias-feed wireless closed loop.
Because the intermediate frequency of the tracking sum-difference link at the inlet of the tracking baseband processing unit has signals, which is equivalent to simulating the condition that the antenna deviates from a target by an angle in the process of calibrating the satellite phase or the antenna tower base tower phase, the tracking baseband processing unit is utilized to calibrate the phase to obtain the relative phase theta under the condition of offset feed wireless closed loop1′≠θ1The sensitivity coefficient under the condition of bias-feed wireless closed loop is k1′≠k1But theta1′-θ1And k1′/k1Are each a relatively fixed value. When the original satellite phase correction result is not available any more due to the change of the equipment combination of the tracking link and the difference link, the great change of the environmental temperature or the replacement of the equipment of the tracking link, and the satellite phase correction needs to be carried out again, the tracking baseband processing unit obtains the relative phase theta under the condition of the bias-feed wireless closed loop through the bias-feed wireless closed loop phase correction2' and coefficient of sensitivity k2', the true relative phase θ at that time can be deduced2And coefficient of sensitivity k2。
In an optional embodiment, taking left-handed rotation as an example, the relative phases and sensitivity coefficients of the space flight measurement and control system in azimuth and pitch are equal, and the initial phase values θ of the two phase shifters0And initial sensitivity coefficient k0The sum signal is sent to a reference signal k of the azimuth phase discriminator0cos(wt+θ0) The reference signal sent to the pitch phase detector is k0sin(wt+θ0) The difference signal is
After high-frequency components are phase-discriminated and low-pass filtered, the output azimuth error voltage
Pitch angle error voltage
The amplitude of the azimuth difference signal and the pitch difference signal of the tracking delta (difference) link are respectively A1(A1Larger indicates that the antenna is further from the target at azimuth angle) and E1(E1The larger the antenna is deviated from the target at the pitch angle, the more the tracking sum (sigma) and difference (delta) link relative phase theta obtained by phase correction1And coefficient of sensitivity k1The tracking baseband can be used for tracking.
Relative phase of sum and difference links
The value is mainly caused by the mutual inconsistency of the phase characteristics of the microwave circuit, the mixer and the intermediate frequency amplifier in the asymmetrical sum and difference links of the feed source structure. The fluctuation of the sensitivity coefficient k value is mainly related to the gain of the sum and difference link devices or the change of the cable insertion loss and the like. The relative phase and gain of the hypothetical sum and difference links are varied by an amount corresponding to the increase in relative phase
If the increment of the relative gain of the differential path is G, the azimuth angle error voltage
Pitch angle error voltage
The following steps are changed: azimuth error voltage
Pitch angle error voltage
Obtaining the relative phase theta of the phase correction result after the phase correction is finished2And coefficient of sensitivity k2Then there is
It can be seen that the relative phase increment can be obtained by other methods
And the specific value of the gain increment G of the sum-difference circuit is obtained, the subsequent correction of the phase of the tower or the fast correction of the phase of the satellite is not needed, and the previous correction result is obtained according to the specific value
And k2＝k1The value calculated by the formula/G can be used for a satellite following task of the system.
In an alternative embodiment, a circularly polarized horn antenna with a gain of about 15dB to 20dB is installed in the main reflector of the main antenna as a bias antenna, the bias antenna is installed in the two sub-reflector supports at a distance from the radius of the antenna edge 1/3, and the main beam is directed to the sub-reflectors of the antenna, so that the multipath interference of the microwave signal is minimized. And then outputting a radio frequency signal with the signal amplitude between 0dBm and-20 dBm by utilizing a radio frequency signal generator which is configured by the aerospace measurement and control system and is positioned at the antenna tower base. The radio frequency signal is sent to the input port of the offset feed antenna through a radio frequency low-loss cable with the length of about 30 meters, the radio frequency signal output by the offset feed antenna enters a feed network after being reflected by a subreflector, a tracking sum path signal and a tracking difference path signal are formed in the feed network, and then the radio frequency signal is sent to a tracking baseband processing unit of an antenna tower base through a low noise amplifier LNA (low noise amplifier) of a tracking sum and delta difference link, a down converter D/C and two equal-length intermediate frequency phase-stabilizing cables L1 and L2. At the moment, signals are all arranged at the intermediate frequency port of the tracking sum-difference link at the input port of the tracking baseband, the intensity of the radio frequency signal output by the radio frequency signal generator is adjusted to enable the amplitude of the sum-path signal at the input port of the tracking baseband processing unit to be between 0dBm and-30 dBm, and the difference-path signal is smaller than the sum-path signal by about 15 dB. The simulation is equivalent to the case that the antenna deviates from the target by an angle in the process of correcting the phase of the satellite.
The low noise amplifier LNA and the down converter D/C respectively connected in series on the sum and difference links send sum and difference signals to the tracking baseband processing unit through the intermediate frequency phase-stable cables L1 and L2, and the difference path is used as a reference, and moves ahead or behind, namely shifts of phases relative to the reference. The tracking sum path signal enters the tracking baseband processing unit through the intermediate frequency phase-stabilizing cable L1, and then the automatic gain control AGC adjustment is first performed to adjust the signal strength to a proper level range. And after the carrier synchronization, the sum path is divided into two paths firstly because the direction and the pitching are orthogonal, wherein one path is used for direction detection, and the other path is used for 90-degree phase shift for pitching detection.
The differential path is divided into two paths after the automatic gain control AGC is controlled, the two paths are respectively used for azimuth detection and pitching detection, a sum path signal used for the azimuth detection is coherently detected with a difference path signal through an azimuth phase shifter, carrier components are filtered, a low-frequency signal containing angle error information is detected, azimuth error voltage synchronous detection is carried out, the azimuth phase shifter is used for carrying out stepping search at intervals of 3 degrees within the range of 0-360 degrees, 121 numerical values of azimuth error voltage are obtained, and the phase shift value theta 'of the azimuth phase shifter corresponding to the largest group of angle error voltage'Az，θ′AzNamely the relative phase of the system in the direction under the condition of offset feed closed loop; similarly, after the phase shift of 90 deg. of the sum path signal for pitch detection, the coherent detection is carried out by the pitch phase shifter and the other path of difference path signal, the carrier component is filtered out, and the signal content is detectedLow-frequency signals of angle error information are synchronous detection of pitch angle error voltage, the pitch phase shifters are used for stepping search at intervals of 3 degrees within the range of 0-360 degrees to obtain the numerical values of 121 pitch angle error voltages, and the phase shift value theta 'of the pitch phase shifter corresponding to the largest group of angle error voltages'El，θ′ElIs the relative phase of the system in pitch under offset-fed closed-loop conditions.
Tracking baseband processing unit to convert theta'AzAnd θ'ElRespectively placing an azimuth phase shifter and a pitch phase shifter, adjusting sensitivity coefficients of azimuth and pitch according to the azimuth angle and the pitch angle of the antenna which is filled in the tracking baseband processing unit and deviates from a target, so that Ua is Ue is A K (V), and the azimuth phase shift value K 'at the moment'AzAnd a pitch phase shift value k'ElNamely the sensitivity coefficient of the system under the condition of bias-fed closed loop, generally k'Az＝k′ElAnd k 'is'AzAnd k'ElAnd is recorded as the sensitivity coefficient k' of the system under the condition of offset feed. Take the left-hand signal as an example, and square shift phase value theta'Az＝θ′ElPrepared from theta'AzAnd θ'ElAnd is recorded as the relative phase theta' of the system under the condition of offset feed.
By comparing the data of the offset-fed wireless closed-loop phase calibration at different time, the relative phase change and the relative gain change of the system tracking sigma-sum and delta-difference links in the period of time can be monitored.
After the aerospace measurement and control system is installed and united, the satellite is corrected to obtain a phase correction result theta1And k1At this time, the method of the invention is adopted and the steps are referred to perform primary offset feed wireless closed loop phase calibration to obtain theta under the condition of self closed loop of the system1' and k1′。θ1' and theta1K is1' and k1There is a fixed relationship between them. When the satellite phase correction result is not available due to the fact that the equipment combination is changed, the environment temperature is greatly changed or the module is replaced, through the method, the phase correction result theta under the self-closed-loop condition of the system is obtained by referring to the steps and performing the bias-feed wireless closed-loop phase correction again2' and k2' if the sum (sigma) and difference (delta) link relative phases can be deduced at the moment of the system tracking
Coefficient of sensitivity k2＝k1/G＝k1/(k1′/k2') will be relatively phase θ2And coefficient of sensitivity k2The tracking baseband is arranged to be used for tracking the satellite, so that the satellite is prevented from correcting the phase and tracking the satellite based on the bias-feed wireless closed loop.
The foregoing is directed to the preferred embodiment of the present invention and it is noted that the above-mentioned embodiments illustrate rather than limit the invention, and that those skilled in the art will be able to design alternative embodiments without departing from the scope of the appended claims. It will be apparent to those skilled in the art that various modifications and improvements can be made without departing from the spirit and substance of the invention, and these modifications and improvements are also considered to be within the scope of the invention.
Claims (10)
1. An offset-fed wireless closed-loop self-tracking phase correction system, comprising: the self-matched radio frequency signal generator of the space flight measurement and control system and the satellite application system, the parabolic antenna used by the space flight measurement and control system and the satellite application system, the offset feed horn antenna installed in the main reflecting surface of the parabolic antenna, the feed network positioned in the main reflecting surface of the antenna and the central body of the antenna, the low noise amplifier and the down converter in the central body, the equal-length phase-stable cables L1 and L2 from the central body of the antenna to the tower base of the antenna, and the tracking base band positioned at the tower base of the antenna, and is characterized in that: the radio frequency signal output by the radio frequency signal generator positioned at the antenna tower base is transmitted to the offset feed horn antenna arranged in the main reflecting surface of the parabolic antenna through the long cable, the radio frequency signal radiated by the offset feed horn antenna is reflected by the auxiliary reflecting surface of the parabolic antenna and then sequentially enters the feed network, tracking sum and difference signals are formed in the feed network, the sum and difference signals reach the antenna central body, are amplified by a low noise amplifier LNA1 and a low noise amplifier LNA2 which are respectively connected in series on a sum link and a difference link in the antenna central body, and are down-converted and amplified by a down converter D/C1 and a down converter D/C2 on the sum link and the difference link, then sent to a tracking baseband processing unit positioned below the antenna tower base through two equal-length intermediate frequency phase-stabilizing cables L1 and L2, thereby forming a dual-channel self-tracking offset feed wireless closed-loop self-tracking phase correction system connected between the feed network and the tracking baseband processing unit; the bias-feed wireless closed-loop self-tracking phase correction system is used for monitoring the relative phase and relative gain change of the tracking sum-difference link, the relative phase theta and the sensitivity coefficient k of the tracking sum-difference link of the space measurement and control system or the satellite application system are calculated under the condition that the satellite is not corrected, and the calculated relative phase theta and the sensitivity coefficient k of the tracking sum-difference link are arranged in the tracking baseband processing unit, so that the correction-free phase tracking of the satellite in the S, C, X frequency band is realized.
2. The offset-fed wireless closed-loop self-tracking phase correction system of claim 1, wherein: the tracking baseband processing unit includes: a D/C and link Automatic Gain Control (AGC) circuit connected with the D/C of the link down converter, a carrier synchronization unit connected in series, a D/C difference link Automatic Gain Control (AGC) circuit connected with the D/C of the difference link down converter, two coherent detectors connected after the D/C difference link automatic gain control, and an azimuth phase shifter and a pitching phase shifter respectively connected with the two coherent detectors and connected with the azimuth branch and the pitching branch of the carrier synchronization unit.
3. The offset-fed wireless closed-loop self-tracking phase correction system of claim 1, wherein: tracking the base band, respectively controlling the gains of the sum and difference links by using the control voltage output by the AGC control circuit on the sum link, and adjusting the position reference signal k after the AGC gain adjustment0cos(wt+θ0) Sending the signal to a direction phase discriminator to perform phase discrimination with a difference signal u delta (t), and adjusting the AGC gain of the pitching reference signal k0sin(wt+θ0) Sending the signal to a pitching phase discriminator to perform phase discrimination with a difference signal u delta (t), and performing low-pass filtering on the azimuth signal subjected to phase discrimination by a filter connected in series to remove high-frequency components to obtain an azimuth error voltage signal
The pitch angle error voltage signal of the phase-discriminated pitch signal after high-frequency components are removed through low-pass filtering of the pitch signal by the series-connected filter
Wherein k is0The sensitivity coefficient of the tracking baseband is put in during the initial phase correction, theta represents the initial phase shift value of the azimuth phase shifter and the pitch phase shifter,
is the relative phase of the sum and difference links.
4. The offset-fed wireless closed-loop self-tracking phase correction system of claim 1, wherein: when correcting phase, the tracking baseband processing unit firstly finds out the phase value theta of the azimuth phase shifter by step-by-step adjustment
The angular error voltage output by the azimuth branch is maximized, and then the sensitivity coefficient K is determined according to the directional sensitivityAZAdjusting the maximum azimuth angle error voltage Ua to a predetermined value, and then finding out the maximum azimuth angle error voltage Ua by adjusting the phase value theta of the pitch phase shifter in a stepping manner
The angular error voltage output by the pitching branch is maximized, and then the sensitivity coefficient K is determined according to the directional sensitivityE1And adjusting the maximum pitching angle error voltage Ue to a given value.
5. The offset-fed wireless closed-loop self-tracking phase correction system of claim 1, wherein: signals of tracking difference (delta) link in azimuth during phase calibration of space measurement and control system
Tracking difference (delta) link in pitchOf (2) a signal
For the relative phase of the sum and difference link, the sigma (sum) link signals are tracked: u ∑ (t) ═ cos (wt), tracking Δ (difference) link signals:
plus or minus when the left-handed signal is positive, plus or minus when the right-handed signal is negative, wherein: u ∑ (t) is a function of the sum signal over time, u Δ (t) is a function of the difference signal over time, a is the magnitude of the difference signal in azimuth, E is the magnitude of the difference signal in pitch, w is the angular frequency, w ═ 2 π f, f is the frequency of the tracking baseband ingress intermediate frequency and the difference signal.
6. The offset-fed wireless closed-loop self-tracking phase correction system of claim 1, wherein: the tracking baseband processing unit carries out phase correction to obtain the relative phase theta of a tracking sum-difference link under the condition of an offset-fed wireless closed loop1' and coefficient of sensitivity k1′，θ1′≠θ1And k is1′≠k1，θ1And k1Relative phases and sensitivity coefficients of tracking sum and difference links under the condition of satellite phase correction are respectively obtained; after the relative phase and the sensitivity coefficient of the tracking sum-difference link are changed, the tracking baseband processing unit monitors the relative phase and the relative gain change of the tracking sum-difference link based on the bias-feed wireless closed loop to obtain the relative phase theta of the tracking sum-difference link under the condition of the bias-feed wireless closed loop at the moment2' and coefficient of sensitivity k2' the relative phase theta of the system tracking sum and difference links at that time is deduced2＝θ1+(θ2′-θ1') and sensitivity coefficient k2＝k1*k2′/k1', at θ1、θ1′、θ2′、k1、k1′、k2' in the known case, the relative phase θ of the sum and difference links will be tracked2And coefficient of sensitivity k2The tracking baseband is arranged to be used for the satellite tracking task, so that the satellite phase correction-free tracking is realized based on the bias-feed wireless closed loop.
7. The offset-fed wireless closed-loop self-tracking phase correction system of claim 1, wherein: the relative phase and gain of the sum and difference links are changed, and the relative phase is increased by
If the increment of the relative gain of the differential path is G, the azimuth angle error voltage
Pitch angle error voltage
The following steps are changed: azimuth error voltage
Pitch angle error voltage
Obtaining the relative phase theta of the tracking sum and difference link after the phase correction is finished2And coefficient of sensitivity k2Then there is
k2＝k1/G。
8. The offset-fed wireless closed-loop self-tracking phase correction system of claim 1, wherein: a circularly polarized horn antenna with the gain of 15 dB-20 dB is used as a bias feed antenna to be arranged in a main reflecting surface of a main antenna, the bias feed antenna is arranged at a position in two sub reflecting surface supporting frames at a distance of 1/3 radius from the edge of the antenna, a main beam is aligned to the sub reflecting surface of the antenna, then a radio frequency signal generator arranged by a space measurement and control system and positioned at an antenna tower base is utilized to output a radio frequency signal with the signal amplitude of 0 dBm-20 dBm, the radio frequency signal is sent to an input port of the bias feed antenna through a cable, the radio frequency signal output by the bias feed antenna enters a feed source network after being reflected by the sub reflecting surface, a tracking sum path and a difference path signal are formed in the feed source network, and then the signals are sent to a tracking baseband processing unit of the antenna tower base through a Low Noise Amplifier (LNA) of a tracking sum sigma-delta difference link, a down converter (D/C) and two medium frequency phase stabilizing cables (L, at the moment, signals are all arranged at the intermediate frequency ports of the tracking sum and difference links at the input port of the tracking baseband, the intensity of the radio frequency signals output by the radio frequency signal generator is adjusted, the amplitude of sum-path signals at the input port of the tracking baseband processing unit is enabled to be between 0dBm and-30 dBm, the difference-path signals are 15dB smaller than the sum-path signals, and the situation that an antenna deviates from a target by an angle in the phase correction process of the analog satellite is the same at the moment.
9. The offset-fed wireless closed-loop self-tracking phase correction system of claim 1, wherein: the low noise amplifier LNA and the down converter D/C which are respectively connected in series on the sum link and the difference link send signals of a sum path and a difference path to the tracking baseband processing unit through medium-frequency phase-stabilizing cables L1 and L2, the sum path and the difference path take the movement of a leading phase or a lagging phase relative to the reference, and after the signals of the tracking sum path enter the tracking baseband processing unit through the medium-frequency phase-stabilizing cable L1, automatic gain control AGC adjustment is firstly carried out, and the signal intensity is adjusted to a proper level range; and after the carrier synchronization, the sum path is divided into two paths, wherein one path is used for azimuth detection, and the other path is used for 90-degree phase shift for pitch detection.
10. The offset-fed wireless closed-loop self-tracking phase correction system of claim 1, wherein: differential path after AGC controlDividing the signal into two paths, respectively using for azimuth detection and pitching detection, coherent detection is carried out on the sum path signal used for azimuth detection and the difference path signal through an azimuth phase shifter, filtering carrier components, detecting a low-frequency signal containing angular error information, synchronous detection is carried out on azimuth error voltage, the azimuth phase shifter is in a range of 0-360 DEG, step search is carried out at intervals of 3 DEG to obtain 121 numerical values of azimuth error voltage, and the phase shift value theta 'of the azimuth phase shifter corresponding to the largest group of angular error voltage'Az，θ′AzNamely the relative phase of the system in the direction under the condition of offset feed closed loop; similarly, after the phase shift of the sum signal for pitch detection is 90 °, coherent detection is performed by the pitch phase shifter and the other difference signal to filter out the carrier component, and a low-frequency signal containing angle error information is detected, i.e. pitch angle error voltage synchronous detection, the pitch phase shifter is step-searched at 3 ° intervals within the range of 0 ° to 360 ° to obtain 121 values of pitch angle error voltages, and the phase shift value θ 'of the pitch phase shifter corresponding to the largest set of angle error voltages'El，θ′ElIs the relative phase of the system in pitch under offset-fed closed-loop conditions.
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