CN110849358A - Measuring device, measuring method and mounting method for phase center of array antenna - Google Patents
Measuring device, measuring method and mounting method for phase center of array antenna Download PDFInfo
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- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
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Abstract
本发明公开了一种阵列天线相位中心的测量装置、测量方法及安装方法。包括FBG传感系统、高精度惯性器件、低精度惯性器件、相控阵列天线与DPCS导航计算机；所述FBG传感系统包括均匀布置在两侧机翼蒙皮表面的FBG传感器阵列；所述高精度惯性器件布置于机舱内部；所述低精度惯性器件包括两个，对称布置于机翼两端处；所述相控阵列天线均匀对称布置在机翼两侧；所述DPCS导航计算机用于解算高精度惯性器件和低精度惯性器件的位姿信息。其能在动态环境下，实时高精度的获取阵列天线相位中心的位姿变化情况，成本低，可靠性高。
The invention discloses a measuring device, measuring method and installation method for the phase center of an array antenna. It includes FBG sensing system, high-precision inertial device, low-precision inertial device, phased array antenna and DPCS navigation computer; the FBG sensing system includes FBG sensor arrays evenly arranged on both sides of the wing skin surface; The precision inertial devices are arranged inside the nacelle; the low-precision inertial devices include two, which are symmetrically arranged at both ends of the wing; the phased array antennas are evenly and symmetrically arranged on both sides of the wing; the DPCS navigation computer is used for solving Calculate the pose information of high-precision inertial devices and low-precision inertial devices. It can acquire the position and attitude change of the phase center of the array antenna with high precision in real time in a dynamic environment, with low cost and high reliability.
Description
技术领域：Technical field:
本发明涉及一种机载阵列天线相位中心的测量方法，具体涉及一种阵列天线相位中心的测量装置、测量方法及安装方法。The invention relates to a method for measuring the phase center of an airborne array antenna, in particular to a measuring device, a measuring method and an installation method for the phase center of an array antenna.
背景技术：Background technique:
机载高分辨率对地观测系统是利用运动成像载荷获取地球表面的高精度空间信息的一种综合性技术，这对重大自然灾害监测及预警，解决人类面临的环境恶化、灾害频发等一系列重大问题具有重要意义。The airborne high-resolution earth observation system is a comprehensive technology that uses motion imaging payloads to obtain high-precision spatial information on the earth's surface. A series of major issues are of great significance.
其中，机载阵列天线的相位中心的测量直接影响到对地观测系统成像分辨率。然而，机载平台飞行时抖动剧烈；载荷天线会随着机翼的挠曲变形、颤振等产生随机抖动误差，从而各子天线间相对运动关系无法精准确定。为此，需要对分布式各天线的运动参数和各阵元天线间的相位中心进行精确测量，以提高对地观测系统成像分辨率。Among them, the measurement of the phase center of the airborne array antenna directly affects the imaging resolution of the earth observation system. However, the airborne platform vibrates violently during flight; the payload antenna will generate random jitter errors with the deflection and flutter of the wing, so the relative motion relationship between the sub-antennas cannot be accurately determined. To this end, it is necessary to accurately measure the motion parameters of the distributed antennas and the phase centers between the antennas of each array element, so as to improve the imaging resolution of the Earth observation system.
发明内容SUMMARY OF THE INVENTION
本发明的目的是提供一种阵列天线相位中心的测量装置、测量方法及安装方法，其能在动态环境下，实时高精度的确定相控阵列天线的相位中心。The purpose of the present invention is to provide a measuring device, measuring method and installation method for the phase center of the array antenna, which can determine the phase center of the phased array antenna with high precision in real time in a dynamic environment.
上述的目的通过以下技术方案实现：The above purpose is achieved through the following technical solutions:
一种阵列天线相位中心的测量装置，包括FBG传感系统、高精度惯性器件、低精度惯性器件、相控阵列天线与DPCS导航计算机；所述FBG传感系统包括均匀布置在两侧机翼蒙皮表面的FBG传感器阵列；所述高精度惯性器件布置于机舱内部；所述低精度惯性器件包括两个，对称布置于机翼两端处；所述相控阵列天线均匀对称布置在机翼两侧；所述DPCS导航计算机用于解算高精度惯性器件和低精度惯性器件的位姿信息。A measuring device for the phase center of an array antenna, including a FBG sensing system, a high-precision inertial device, a low-precision inertial device, a phased array antenna and a DPCS navigation computer; the FBG sensing system includes a wing mask evenly arranged on both sides. The FBG sensor array on the skin surface; the high-precision inertial device is arranged inside the nacelle; the low-precision inertial device includes two, symmetrically arranged at both ends of the wing; the phased array antenna is evenly and symmetrically arranged on both sides of the wing. side; the DPCS navigation computer is used to solve the pose information of the high-precision inertial device and the low-precision inertial device.
所述的阵列天线相位中心的测量装置，所述FBG传感器阵列中相邻两条FBG传感器的间距根据iFEM法分析确定，上下蒙皮处所对应的FBG传感器阵列是连续接通的。In the device for measuring the phase center of the array antenna, the distance between two adjacent FBG sensors in the FBG sensor array is determined by iFEM analysis, and the FBG sensor arrays corresponding to the upper and lower skins are continuously connected.
本发明的另一目的是提供一种上述阵列天线相位中心的测量装置的安装方法，包括如下步骤：Another object of the present invention is to provide a method for installing the above-mentioned measuring device for the phase center of the array antenna, comprising the following steps:
步骤一、确定机翼的类型，根据基于RZT理论的iFEM法划出FBG传感器阵列的走线；Step 1. Determine the type of the wing, and draw the wiring of the FBG sensor array according to the iFEM method based on the RZT theory;
步骤二、在机翼的上侧蒙皮和下侧蒙皮走线处采用无封装裸贴的形式粘贴FBG传感器阵列；Step 2. Paste the FBG sensor array in the form of unpackaged bare stickers on the upper and lower skins of the wing;
步骤三、将FBG传感器阵列端部接口与光纤光栅解调仪连接，光纤光栅解调仪与计算机连接；Step 3: Connect the end interface of the FBG sensor array to the fiber grating demodulator, and the fiber grating demodulator is connected to the computer;
步骤四、在机翼两端的下侧蒙皮处，首先确定低精度惯性器件的安装位置，在低精度惯性器件和安装位置中间设置减振装置，通过数据串口线分别与电源以及DPCS导航计算机连接；Step 4. At the lower skins at both ends of the wing, first determine the installation position of the low-precision inertial device, set up a vibration damping device between the low-precision inertial device and the installation position, and connect to the power supply and the DPCS navigation computer through the data serial cable respectively. ;
步骤五、将高精度惯性器件安装于机舱内部与机翼两端连线的中点的位置处，通过数据串口线分别与电源以及DPCS导航计算机连接；Step 5. Install the high-precision inertial device at the position of the midpoint of the connection between the interior of the nacelle and the two ends of the wing, and connect to the power supply and the DPCS navigation computer respectively through the data serial line;
步骤六、在机翼两端的下侧蒙皮处，确定相控阵列天线的安装位置，在相控阵列天线和安装位置中间设置减振装置，通过数据串口线分别与电源以及雷达控制组件连接；Step 6. Determine the installation position of the phased array antenna at the lower skins at both ends of the wing, set up a vibration damping device between the phased array antenna and the installation position, and connect to the power supply and the radar control component respectively through the data serial cable;
步骤七、将DPCS导航计算机以及雷达控制组件与终端处理计算机连接，调试设备，验证是否连接正常，安装完成。Step 7. Connect the DPCS navigation computer and the radar control component to the terminal processing computer, debug the equipment, verify whether the connection is normal, and the installation is complete.
本发明的再一目的是提供一种用上述阵列天线相位中心的测量装置的进行阵列天线相位中心测量的方法，包括如下步骤：Another object of the present invention is to provide a method for measuring the phase center of an array antenna using the above-mentioned measuring device for the phase center of the array antenna, comprising the following steps:
步骤一、检验各个部件之间的数据线数据采集功能是否正常，检验在飞机上所选设备部件的总重量是否超重，完成飞行测试前的检测；Step 1. Check whether the data collection function of the data line between each component is normal, check whether the total weight of the selected equipment components on the aircraft is overweight, and complete the inspection before the flight test;
步骤二、试验飞机起飞前，利用RPS基准点测量系统获取飞机机翼自然下垂时的杆臂值,用于确实初始时的参考坐标系；Step 2. Before the test aircraft takes off, use the RPS reference point measurement system to obtain the lever arm value when the aircraft wing sags naturally, which is used to determine the initial reference coordinate system;
步骤三、试验飞机起飞，飞行过程中，机翼抖动变形，FBG传感器阵列中的波长值发生变化，通过数学模型拟合得出机翼的动态变化曲线，为低精度惯性器件提供参考坐标系；Step 3. The test aircraft takes off. During the flight, the wing shakes and deforms, and the wavelength value in the FBG sensor array changes. The dynamic change curve of the wing is obtained through mathematical model fitting, which provides a reference coordinate system for low-precision inertial devices;
步骤四、低精度惯性器件和高精度惯性器件工作，通过DPCS导航计算机的解算，获取飞行状态下惯性器件的空间位置和姿态信息；Step 4. The low-precision inertial device and the high-precision inertial device work, and the spatial position and attitude information of the inertial device in the flight state are obtained through the calculation of the DPCS navigation computer;
步骤五、结合拟合的机翼动态变化曲线和高、低精度惯性器件的位姿信息，获得各相控阵列天线在机翼各节点的真实动态变化情况，即获取相控阵列天线的相位中心。Step 5: Combine the fitted dynamic change curve of the wing and the pose information of the high- and low-precision inertial devices to obtain the real dynamic changes of each phased array antenna at each node of the wing, that is, to obtain the phase center of the phased array antenna .
有益效果：本发明的装置将FBG传感系统和高、低惯性器件的功能组合，结合了二者的优点，将两者数据信息融合，通过计算机的处理，高精度测得在动态环境中的机载相控阵列天线的位姿信息，本发明也适合静态下机载相控阵列天线的位姿信息；Beneficial effect: the device of the present invention combines the functions of the FBG sensing system and the high and low inertia devices, combines the advantages of the two, fuses the data information of the two, and through the processing of the computer, can measure the high precision in the dynamic environment. The position and attitude information of the airborne phased array antenna, the present invention is also suitable for statically downloading the position and attitude information of the airborne phased array antenna;
另外，该装置所选型号的FBG传感器阵列以及低精度惯性器件尺寸小、重量轻、成本低、布置个数少，对大尺寸机翼以及机身产生的影响可忽略不计，高精度惯性器件尺寸小、重量轻、布置个数少、精度高，通过FBG传感系统、高低精度惯性器件组合的方式，测量相控阵列天线的相位中心，其测量精确。In addition, the FBG sensor array and low-precision inertial device of the selected model of the device are small in size, light in weight, low in cost, and small in number of layouts, so the impact on large-sized wings and fuselage is negligible, and the size of the high-precision inertial device is negligible. It is small, light in weight, small in number of layouts and high in precision. The phase center of the phased array antenna is measured by the combination of FBG sensing system and high and low precision inertial devices, and the measurement is accurate.
附图说明Description of drawings
图1是高低精度惯性器件及阵列天线布局示意图；Figure 1 is a schematic diagram of the layout of high and low precision inertial devices and array antennas;
图2是FBG传感器阵列布局示意图。Figure 2 is a schematic diagram of the layout of the FBG sensor array.
图中，1-高精度惯性器件，21、22为飞机两端的低精度惯性器件，31、32、33、34、35、36为各个相控阵列天线，41、42、43、44、45、46为各个FBG传感器阵列。In the figure, 1-high-precision inertial device, 21, 22 are low-precision inertial devices at both ends of the aircraft, 31, 32, 33, 34, 35, 36 are phased array antennas, 41, 42, 43, 44, 45, 46 is each FBG sensor array.
具体实施方式Detailed ways
如图1-2所示，一种阵列天线相位中心的测量装置，包括FBG传感系统、高精度惯性器件、低精度惯性器件、相控阵列天线与DPCS导航计算机；所述FBG传感系统包括均匀布置在两侧机翼蒙皮表面的FBG传感器阵列；所述高精度惯性器件布置于机舱内部；所述低精度惯性器件包括两个，对称布置于机翼两端处；所述相控阵列天线均匀对称布置在机翼两侧；所述DPCS导航计算机用于解算高精度惯性器件和低精度惯性器件的位姿信息。As shown in Figure 1-2, an array antenna phase center measurement device includes a FBG sensing system, a high-precision inertial device, a low-precision inertial device, a phased array antenna and a DPCS navigation computer; the FBG sensing system includes FBG sensor arrays evenly arranged on both sides of the wing skin surface; the high-precision inertial device is arranged inside the nacelle; the low-precision inertial device includes two, symmetrically arranged at both ends of the wing; the phased array The antennas are evenly and symmetrically arranged on both sides of the wing; the DPCS navigation computer is used to calculate the position and attitude information of the high-precision inertial device and the low-precision inertial device.
所述FBG传感器阵列中相邻两条FBG传感器的间距根据iFEM法分析确定，上下蒙皮处所对应的FBG传感器阵列是连续接通的。The distance between two adjacent FBG sensors in the FBG sensor array is determined according to the analysis by the iFEM method, and the FBG sensor arrays corresponding to the upper and lower skins are continuously connected.
上述阵列天线相位中心的测量装置的安装方法，包括如下步骤：The installation method of the above-mentioned measuring device for the phase center of the array antenna includes the following steps:
步骤一、确定机翼的类型，根据基于RZT理论的iFEM法划出FBG传感器阵列的走线；Step 1. Determine the type of the wing, and draw the wiring of the FBG sensor array according to the iFEM method based on the RZT theory;
步骤二、在机翼的上侧蒙皮和下侧蒙皮走线处采用无封装裸贴的形式粘贴FBG传感器阵列；Step 2. Paste the FBG sensor array in the form of unpackaged bare stickers on the upper and lower skins of the wing;
步骤三、将FBG传感器阵列端部接口与光纤光栅解调仪连接，光纤光栅解调仪与计算机连接；Step 3: Connect the end interface of the FBG sensor array to the fiber grating demodulator, and the fiber grating demodulator is connected to the computer;
步骤四、在机翼两端的下侧蒙皮处，首先确定低精度惯性器件的安装位置，在低精度惯性器件和安装位置中间设置减振装置，通过数据串口线分别与电源以及DPCS导航计算机连接；Step 4. At the lower skins at both ends of the wing, first determine the installation position of the low-precision inertial device, set up a vibration damping device between the low-precision inertial device and the installation position, and connect to the power supply and the DPCS navigation computer through the data serial cable respectively. ;
步骤五、将高精度惯性器件安装于机舱内部与机翼两端连线的中点的位置处，通过数据串口线分别与电源以及DPCS导航计算机连接；Step 5. Install the high-precision inertial device at the position of the midpoint of the connection between the interior of the nacelle and the two ends of the wing, and connect to the power supply and the DPCS navigation computer respectively through the data serial line;
步骤六、在机翼两端的下侧蒙皮处，确定相控阵列天线的安装位置，在相控阵列天线和安装位置中间设置减振装置，通过数据串口线分别与电源以及雷达控制组件连接；Step 6. Determine the installation position of the phased array antenna at the lower skins at both ends of the wing, set up a vibration damping device between the phased array antenna and the installation position, and connect to the power supply and the radar control component respectively through the data serial cable;
步骤七、将DPCS导航计算机以及雷达控制组件与终端处理计算机连接，调试设备，验证是否连接正常，安装完成。Step 7. Connect the DPCS navigation computer and the radar control component to the terminal processing computer, debug the equipment, verify whether the connection is normal, and the installation is complete.
本发明的再一目的是提供一种用上述阵列天线相位中心的测量装置的进行阵列天线相位中心测量的方法，包括如下步骤：Another object of the present invention is to provide a method for measuring the phase center of an array antenna using the above-mentioned measuring device for the phase center of the array antenna, comprising the following steps:
步骤一、检验各个部件之间的数据线数据采集功能是否正常，检验在飞机上所选设备部件的总重量是否超重，完成飞行测试前的检测；Step 1. Check whether the data collection function of the data line between each component is normal, check whether the total weight of the selected equipment components on the aircraft is overweight, and complete the inspection before the flight test;
步骤二、试验飞机起飞前，利用RPS基准点测量系统获取飞机机翼自然下垂时的杆臂值,用于确实初始时的参考坐标系；Step 2. Before the test aircraft takes off, use the RPS reference point measurement system to obtain the lever arm value when the aircraft wing sags naturally, which is used to determine the initial reference coordinate system;
步骤三、试验飞机起飞，飞行过程中，机翼抖动变形，FBG传感器阵列中的波长值发生变化，通过数学模型拟合得出机翼的动态变化曲线，为低精度惯性器件提供参考坐标系；Step 3. The test aircraft takes off. During the flight, the wing shakes and deforms, and the wavelength value in the FBG sensor array changes. The dynamic change curve of the wing is obtained through mathematical model fitting, which provides a reference coordinate system for low-precision inertial devices;
步骤四、低精度惯性器件和高精度惯性器件工作，通过DPCS导航计算机的解算，获取飞行状态下惯性器件的空间位置和姿态信息；Step 4. The low-precision inertial device and the high-precision inertial device work, and the spatial position and attitude information of the inertial device in the flight state are obtained through the calculation of the DPCS navigation computer;
步骤五、结合拟合的机翼动态变化曲线和高、低精度惯性器件的位姿信息，获得各相控阵列天线在机翼各节点的真实动态变化情况，即获取相控阵列天线的相位中心。Step 5: Combine the fitted dynamic change curve of the wing and the pose information of the high- and low-precision inertial devices to obtain the real dynamic changes of each phased array antenna at each node of the wing, that is, to obtain the phase center of the phased array antenna .
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112100735A (en) * | 2020-08-03 | 2020-12-18 | 东南大学 | Airborne IMU high-precision reference acquisition method based on wing deformation |
| CN114267935A (en) * | 2021-12-14 | 2022-04-01 | 重庆交通大学绿色航空技术研究院 | Bidirectional communication array antenna applied to unmanned aerial vehicle and communication method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0940690A2 (en) * | 1998-03-05 | 1999-09-08 | The Whitaker Corporation | Microwave sensor for object motion detection |
| CN103064089A (en) * | 2012-12-28 | 2013-04-24 | 中国电子科技集团公司第五十四研究所 | Method for calibrating satellite navigation digital multi-beam launching array antenna phase center |
| CN103389497A (en) * | 2012-05-11 | 2013-11-13 | 中国科学院电子学研究所 | Airborne thinned array antenna downward-looking three-dimensional imaging radar system and imaging method |
| CN103439263A (en) * | 2013-08-06 | 2013-12-11 | 南京航空航天大学 | Monitoring method and monitoring system for progressive damage of corrugated composite wing cover |
| CN103682677A (en) * | 2013-11-14 | 2014-03-26 | 中国科学院电子学研究所 | Airship radar conformal thinned array antenna and its signal processing method |
| CN207198335U (en) * | 2017-08-29 | 2018-04-06 | 中国地震局第一监测中心 | Continuous rotary process gps antenna phase center detecting system |
-
2019
- 2019-11-08 CN CN201911088318.9A patent/CN110849358B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0940690A2 (en) * | 1998-03-05 | 1999-09-08 | The Whitaker Corporation | Microwave sensor for object motion detection |
| CN103389497A (en) * | 2012-05-11 | 2013-11-13 | 中国科学院电子学研究所 | Airborne thinned array antenna downward-looking three-dimensional imaging radar system and imaging method |
| CN103064089A (en) * | 2012-12-28 | 2013-04-24 | 中国电子科技集团公司第五十四研究所 | Method for calibrating satellite navigation digital multi-beam launching array antenna phase center |
| CN103439263A (en) * | 2013-08-06 | 2013-12-11 | 南京航空航天大学 | Monitoring method and monitoring system for progressive damage of corrugated composite wing cover |
| CN103682677A (en) * | 2013-11-14 | 2014-03-26 | 中国科学院电子学研究所 | Airship radar conformal thinned array antenna and its signal processing method |
| CN207198335U (en) * | 2017-08-29 | 2018-04-06 | 中国地震局第一监测中心 | Continuous rotary process gps antenna phase center detecting system |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112100735A (en) * | 2020-08-03 | 2020-12-18 | 东南大学 | Airborne IMU high-precision reference acquisition method based on wing deformation |
| CN114267935A (en) * | 2021-12-14 | 2022-04-01 | 重庆交通大学绿色航空技术研究院 | Bidirectional communication array antenna applied to unmanned aerial vehicle and communication method |
| CN114267935B (en) * | 2021-12-14 | 2023-11-07 | 重庆交通大学绿色航空技术研究院 | Bidirectional communication array antenna and communication method applied to unmanned aerial vehicle |
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