CN110849358B - Measuring device, measuring method and mounting method for array antenna phase center - Google Patents
Measuring device, measuring method and mounting method for array antenna phase center Download PDFInfo
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- CN110849358B CN110849358B CN201911088318.9A CN201911088318A CN110849358B CN 110849358 B CN110849358 B CN 110849358B CN 201911088318 A CN201911088318 A CN 201911088318A CN 110849358 B CN110849358 B CN 110849358B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C21/00—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00
- G01C21/10—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration
- G01C21/12—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration executed aboard the object being navigated; Dead reckoning
- G01C21/16—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration executed aboard the object being navigated; Dead reckoning by integrating acceleration or speed, i.e. inertial navigation
- G01C21/165—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by using measurements of speed or acceleration executed aboard the object being navigated; Dead reckoning by integrating acceleration or speed, i.e. inertial navigation combined with non-inertial navigation instruments
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- 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
- G01S13/02—Systems using reflection of radio waves, e.g. primary radar systems; Analogous systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- 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
- G01S13/02—Systems using reflection of radio waves, e.g. primary radar systems; Analogous systems
- G01S13/06—Systems determining position data of a target
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
- G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
- G01S7/40—Means for monitoring or calibrating
- G01S7/4004—Means for monitoring or calibrating of parts of a radar system
- G01S7/4021—Means for monitoring or calibrating of parts of a radar system of receivers
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- 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
- G01S13/02—Systems using reflection of radio waves, e.g. primary radar systems; Analogous systems
- G01S2013/0236—Special technical features
- G01S2013/0245—Radar with phased array antenna
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Abstract
The invention discloses a measuring device, a measuring method and an installation method of an array antenna phase center. The FBG sensor comprises an 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 comprises FBG sensor arrays which are uniformly arranged on the surfaces of wing skins on two sides; the high-precision inertial device is arranged inside the cabin; the low-precision inertia devices comprise two low-precision inertia devices which are symmetrically arranged at two ends of the wing; the phased array antennas are uniformly and symmetrically arranged on two sides of the wing; the DPCS navigation computer is used for resolving pose information of the high-precision inertial device and the low-precision inertial device. The method can acquire the pose change condition of the phase center of the array antenna in real time and high precision in a dynamic environment, and is low in cost and high in reliability.
Description
The technical field is as follows:
the invention relates to a method for measuring a phase center of an airborne array antenna, in particular to a device, a method and a method for measuring the phase center of the array antenna.
Background art:
the airborne high-resolution earth observation system is a comprehensive technology for acquiring high-precision spatial information on the earth surface by using a motion imaging load, and has important significance for monitoring and early warning natural disasters and solving a series of major problems of environmental deterioration, frequent occurrence of disasters and the like faced by human beings.
Wherein, the measurement of the phase center of the airborne array antenna directly influences the imaging resolution of the earth observation system. However, airborne platforms are subject to severe jitter when flying; the load antenna generates random jitter errors along with the deflection deformation, flutter and the like of the wing, so that the relative motion relation among all the sub-antennas cannot be accurately determined. Therefore, the motion parameters of each distributed antenna and the phase center between each array element antenna need to be accurately measured so as to improve the imaging resolution of the earth observation system.
Disclosure of Invention
The invention aims to provide a measuring device, a measuring method and an installation method for the phase center of an array antenna, which can determine the phase center of a phased array antenna in real time and with high precision in a dynamic environment.
The above purpose is realized by the following technical scheme:
a measuring device for the phase center of an array antenna comprises an 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 comprises FBG sensor arrays which are uniformly arranged on the surfaces of wing skins on two sides; the high-precision inertial device is arranged inside the cabin; the low-precision inertia devices comprise two low-precision inertia devices which are symmetrically arranged at two ends of the wing; the phased array antennas are uniformly and symmetrically arranged on two sides of the wing; the DPCS navigation computer is used for resolving pose information of the high-precision inertial device and the low-precision inertial device.
According to the measuring device for the array antenna phase center, the distance between two adjacent FBG sensors in the FBG sensor array is analyzed and determined according to an iFEM method, and the FBG sensor arrays corresponding to the upper skin and the lower skin are continuously connected.
Another object of the present invention is to provide a method for installing the measuring apparatus for measuring the phase center of the array antenna, including the following steps:
determining the type of a wing, and drawing wiring of an FBG sensor array according to an iFEM method based on an RZT theory;
step two, sticking the FBG sensor arrays at the routing positions of the upper side skin and the lower side skin of the wing in a non-packaging bare sticking mode;
connecting an end interface of the FBG sensor array with a fiber bragg grating demodulator, and connecting the fiber bragg grating demodulator with a computer;
fourthly, at the lower side skin parts at two ends of the wing, firstly determining the installation position of the low-precision inertia device, arranging a vibration damping device between the low-precision inertia device and the installation position, and respectively connecting the low-precision inertia device and the installation position with a power supply and a DPCS navigation computer through data serial port lines;
installing a high-precision inertial device at the position of the midpoint of a connecting line between the interior of the cabin and the two ends of the wing, and respectively connecting the high-precision inertial device with a power supply and a DPCS navigation computer through data serial port lines;
sixthly, determining the mounting position of the phased array antenna at the lower side skin parts at two ends of the wing, arranging a damping device between the phased array antenna and the mounting position, and respectively connecting the damping device with a power supply and a radar control assembly through data serial port lines;
and seventhly, connecting the DPCS navigation computer and the radar control component with a terminal processing computer, debugging equipment, verifying whether the connection is normal or not, and finishing installation.
Another object of the present invention is to provide a method for measuring the phase center of an array antenna by using the above measuring apparatus for measuring the phase center of an array antenna, comprising the steps of:
step one, checking whether the data acquisition function of a data line between each part is normal, checking whether the total weight of selected equipment parts on an airplane is overweight, and completing detection before a flight test;
before the test airplane takes off, a lever arm value of the airplane wing when the airplane wing naturally sags is obtained by using an RPS datum point measuring system and used for a reference coordinate system in actual initial time;
thirdly, testing the takeoff of the airplane, wherein during the flying process, wings are vibrated and deformed, the wavelength values in the FBG sensor array are changed, and a dynamic change curve of the wings is obtained through mathematical model fitting so as to provide a reference coordinate system for the low-precision inertial device;
working of the low-precision inertial device and the high-precision inertial device, and acquiring the spatial position and attitude information of the inertial device in the flight state through the calculation of a DPCS navigation computer;
and step five, combining the fitted dynamic change curve of the wing and the pose information of the high-precision inertial device and the low-precision inertial device to obtain the real dynamic change condition of each phased array antenna at each node of the wing, namely obtaining the phase center of each phased array antenna.
Has the advantages that: the device combines the functions of the FBG sensing system and the high and low inertia devices, combines the advantages of the FBG sensing system and the high and low inertia devices, fuses data information of the FBG sensing system and the high and low inertia devices, measures the pose information of the airborne phased array antenna in a dynamic environment at high precision through the processing of a computer, and is also suitable for the pose information of the airborne phased array antenna under a static state;
in addition, the FBG sensor array and the low-precision inertial device of the type selected by the device are small in size, light in weight, low in cost and small in arrangement number, the influence on large-size wings and a fuselage is negligible, the high-precision inertial device is small in size, light in weight, small in arrangement number and high in precision, the phase center of the phased array antenna is measured in a mode of combining the FBG sensor system and the high-precision inertial device and the low-precision inertial device, and the measurement is accurate.
Drawings
FIG. 1 is a schematic diagram of a high and low precision inertial device and array antenna layout;
fig. 2 is a schematic diagram of a FBG sensor array layout.
In the figure, 1-high-precision inertial device, 21, 22 are low-precision inertial devices at both ends of the airplane, 31, 32, 33, 34, 35, 36 are each phased array antennas, and 41, 42, 43, 44, 45, 46 are each FBG sensor arrays.
Detailed Description
As shown in fig. 1-2, a measuring device for the phase center of an array antenna comprises an 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 comprises FBG sensor arrays which are uniformly arranged on the surfaces of wing skins on two sides; the high-precision inertial device is arranged inside the engine room; the low-precision inertia devices comprise two low-precision inertia devices which are symmetrically arranged at two ends of the wing; the phased array antennas are uniformly and symmetrically arranged on two sides of the wing; the DPCS navigation computer is used for resolving pose information of the high-precision inertial device and the low-precision inertial device.
The distance between two adjacent FBG sensors in the FBG sensor array is determined according to the analysis of an iFEM method, and the FBG sensor arrays corresponding to the upper skin and the lower skin are continuously connected.
The installation method of the measuring device for the phase center of the array antenna comprises the following steps:
determining the type of a wing, and drawing wiring of an FBG sensor array according to an iFEM method based on an RZT theory;
step two, adhering FBG sensor arrays at the routing positions of upper side skins and lower side skins of the wings in a non-packaging bare mode;
connecting an end interface of the FBG sensor array with a fiber bragg grating demodulator, and connecting the fiber bragg grating demodulator with a computer;
fourthly, at the lower side skin parts at two ends of the wing, firstly determining the installation position of the low-precision inertia device, arranging a vibration damping device between the low-precision inertia device and the installation position, and respectively connecting the low-precision inertia device and the installation position with a power supply and a DPCS navigation computer through data serial port lines;
installing a high-precision inertial device at the position of the midpoint of a connecting line between the interior of the cabin and the two ends of the wing, and respectively connecting the high-precision inertial device with a power supply and a DPCS navigation computer through data serial port lines;
sixthly, determining the installation position of the phased array antenna at the lower side skin parts at the two ends of the wing, arranging a damping device between the phased array antenna and the installation position, and respectively connecting the phased array antenna and the installation position with a power supply and a radar control assembly through data serial port lines;
and seventhly, connecting the DPCS navigation computer and the radar control assembly with a terminal processing computer, debugging equipment, verifying whether the connection is normal or not, and finishing installation.
Still another object of the present invention is to provide a method for measuring the phase center of an array antenna by using the above measuring apparatus for measuring the phase center of an array antenna, comprising the steps of:
step one, checking whether the data acquisition function of a data line between each part is normal, checking whether the total weight of selected equipment parts on an airplane is overweight, and completing detection before a flight test;
before the test airplane takes off, a lever arm value of the airplane wing when the airplane wing naturally sags is obtained by using an RPS datum point measuring system and used for a reference coordinate system in actual initial time;
thirdly, testing the takeoff of the airplane, wherein during the flying process, wings are vibrated and deformed, the wavelength values in the FBG sensor array are changed, and a dynamic change curve of the wings is obtained through mathematical model fitting so as to provide a reference coordinate system for the low-precision inertial device;
working of the low-precision inertial device and the high-precision inertial device, and acquiring spatial position and attitude information of the inertial devices in a flight state through calculation of a DPCS navigation computer;
and step five, combining the fitted wing dynamic change curve and the pose information of the high-precision inertial device and the low-precision inertial device to obtain the real dynamic change condition of each phased array antenna at each node of the wing, namely obtaining the phase center of the phased array antenna.
Claims (2)
1. The installation method of the measuring device of the array antenna phase center comprises an 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 comprises FBG sensor arrays which are uniformly arranged on the surfaces of wing skins on two sides; the high-precision inertial device is arranged inside the cabin; the low-precision inertia devices comprise two low-precision inertia devices which are symmetrically arranged at two ends of the wing; the phased array antennas are uniformly and symmetrically arranged on two sides of the wing; the DPCS navigation computer is used for resolving pose information of the high-precision inertial device and the low-precision inertial device; the method is characterized in that the installation method of the measuring device of the array antenna phase center comprises the following steps:
determining the type of wings, and drawing wiring of an FBG sensor array according to an iFEM method based on an RZT theory;
step two, sticking the FBG sensor arrays at the routing positions of the upper side skin and the lower side skin of the wing in a non-packaging bare sticking mode;
connecting an end interface of the FBG sensor array with a fiber bragg grating demodulator, and connecting the fiber bragg grating demodulator with a computer;
step four, at the lower side skin parts at two ends of the wing, firstly, determining the installation position of the low-precision inertia device, arranging a vibration damping device between the low-precision inertia device and the installation position, and respectively connecting the low-precision inertia device and the installation position with a power supply and a DPCS navigation computer through data serial port lines;
installing a high-precision inertial device at the position of the midpoint of a connecting line between the interior of the cabin and the two ends of the wing, and respectively connecting the high-precision inertial device with a power supply and a DPCS navigation computer through data serial port lines;
sixthly, determining the mounting position of the phased array antenna at the lower side skin parts at two ends of the wing, arranging a damping device between the phased array antenna and the mounting position, and respectively connecting the damping device with a power supply and a radar control assembly through data serial port lines;
and seventhly, connecting the DPCS navigation computer and the radar control component with a terminal processing computer, debugging equipment, verifying whether the connection is normal or not, and finishing installation.
2. A method of making an array antenna phase center measurement using the array antenna phase center measurement apparatus mounted by the method of claim 1, the method comprising the steps of:
step one, checking whether the data acquisition function of a data line between each part is normal, checking whether the total weight of selected equipment parts on an airplane is overweight, and completing detection before a flight test;
before the test airplane takes off, a lever arm value of the airplane wing when the airplane wing naturally sags is obtained by using an RPS datum point measuring system and used for a reference coordinate system in actual initial time;
thirdly, testing the takeoff of the airplane, wherein during the flying process, wings are vibrated and deformed, the wavelength values in the FBG sensor array are changed, and a dynamic change curve of the wings is obtained through mathematical model fitting so as to provide a reference coordinate system for the low-precision inertial device;
working of the low-precision inertial device and the high-precision inertial device, and acquiring the spatial position and attitude information of the inertial device in the flight state through the calculation of a DPCS navigation computer;
and step five, combining the fitted wing dynamic change curve and the pose information of the high-precision inertial device and the low-precision inertial device to obtain the real dynamic change condition of each phased array antenna at each node of the wing, namely obtaining the phase center of the phased array antenna.
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| CN112100735B (en) * | 2020-08-03 | 2022-11-11 | 东南大学 | Airborne IMU high-precision reference acquisition method based on wing deformation |
| 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 applied to unmanned aerial vehicle and communication method |
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| US6087972A (en) * | 1998-03-05 | 2000-07-11 | The Whitaker Corporation | Microwave sensor for object motion detection |
| CN103389497B (en) * | 2012-05-11 | 2015-06-17 | 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 |
| CN103064089B (en) * | 2012-12-28 | 2014-11-05 | 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 |
| CN103682677B (en) * | 2013-11-14 | 2016-07-13 | 中国科学院电子学研究所 | A kind of ship load radar conformal thinned array antenna and signal processing method thereof |
| 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 |
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