Helical wing unmanned aerial vehicle-based transportable reflector antenna phase calibration method

Abstract

The invention discloses a transportable reflector antenna phase calibration method based on a spiral wing unmanned aerial vehicle. The method comprises the following steps that the spiral wing unmanned aerial vehicle carries a signal generator and an emission source antenna to take off to a proper position; the unmanned aerial vehicle transmits a suitable signal, the movable reflector antenna receives the transmitted signal of the unmanned aerial vehicle, and the movable reflector antenna tracks the baseband to lock the transmitted signal of the unmanned aerial vehicle; under the cooperation of a movable reflector antenna tracking base band, antenna servo software is controlled, and a proper antenna phase is debugged, so that the movable reflector antenna can automatically track a transmitting signal of the spiral wing unmanned aerial vehicle; and storing the self-tracking phase of the transportable reflector antenna to a tracking baseband, wherein the phase is the tracking phase of the transportable reflector antenna. The method has the advantages of short period, low cost and high efficiency.

Description

Technical Field

[0001] The present invention belongs to the field of antennas, and particularly relates to a method for phase calibration of a movable reflector antenna based on a quadcopter drone. Background Art

[0002] With the rapid development of electronic information technology, the resolution of satellite observable capabilities has been rapidly improved, and a large amount of generated data needs to be transmitted to ground systems. Ground systems generally use reflector antennas to receive satellite data transmission signals. The movable reflector antenna has the advantages of high gain, good directivity, high mobility, and flexible station layout, and can meet the requirements of various tasks. However, if the movable reflector antenna is not phase-calibrated, the antenna cannot achieve automatic tracking of the satellite, and the received data has a high error rate and poor usability. Therefore, before using the movable reflector antenna, it must be phase-calibrated.

[0003] Currently, the calibration methods used for antennas mainly include calibration tower calibration and satellite calibration. Calibration tower calibration has the characteristics of high environmental requirements and low efficiency. Satellite calibration is limited by bandwidth. Therefore, a method for solving new frequency phase calibration needs to be found. The phase calibration method based on a quadcopter drone solves the problem that calibration can only be performed using a calibration tower, and calibration can be quickly performed under the condition that field test conditions are available. Summary of the Invention

[0004] The purpose of the present invention is to provide a method for phase calibration of a movable reflector antenna based on a quadcopter drone, which has the advantages of short period, low cost, and high efficiency.

[0005] To achieve the above purpose, the technical solution adopted by the present invention is as follows:

[0006] A method for phase calibration of a movable reflector antenna based on a quadcopter drone includes the following steps:

[0007] S1, the quadcopter drone takes off with a signal generator and a transmitting source antenna to a suitable position;

[0008] S2, the drone transmits a suitable signal, the movable reflector antenna receives the transmitted signal of the drone, and the movable reflector antenna tracks and locks the transmitted signal of the drone in the baseband;

[0009] S3, under the cooperation of the baseband tracking of the movable reflector antenna, the antenna servo software is controlled to debug a suitable antenna phase so that the movable reflector antenna can self-track the transmitted signal of the quadcopter drone;

[0010] S4, the phase at which the movable reflector antenna can self-track is saved to the tracking baseband, and this phase is the tracking phase of the movable reflector antenna.

[0011] Preferably, in S1, the UAV and the ground movable reflector antenna are in the same calibration site.

[0012] Preferably, in S1, the suitable positions include the slant range R and the vertical distance H.

[0013] Preferably, in S1, the slant range R satisfies the far-field calibration condition, and the calculation formula is:

[0014] R ≥ 2(D + d)*(D + d) / λ

[0015] Where: D is the aperture of the movable reflector antenna; d is the aperture of the transmitting source antenna; λ is the wavelength corresponding to the operating frequency.

[0016] Preferably, in S1, the vertical distance H satisfies the far-field calibration condition, and the calculation formula is:

[0017] H ≥ R*sin(2*θ0.5)

[0018] Where: R is the slant range; 2*θ0.5 is the half-power beamwidth of the main beam of the movable reflector antenna.

[0019] Preferably, in S1, the helicopter UAV mounts a signal generator and a transmitting source antenna, and the signal output by the signal generator is connected to the transmitting source antenna.

[0020] Preferably, the specific steps of S2 are:

[0021] S201, the transmitting source antenna of the UAV points to the movable reflector antenna;

[0022] S202, the movable reflector antenna points to the transmitting source antenna of the UAV;

[0023] S203, the signal generator of the UAV transmits a signal, the movable reflector antenna receives the signal of the UAV, and the movable reflector antenna tracks and locks the transmitted signal of the UAV at the baseband.

[0024] Preferably, the specific steps of S3 are:

[0025] S301, control the movable reflector antenna to deflect the antenna azimuth so that the azimuth of the movable reflector antenna deflects towards the positive half-axis, the azimuth error voltage is negative, and the azimuth-elevation cross-coupling is less than 1 / 5;

[0026] S302, control the movable reflector antenna to deflect the antenna azimuth so that the azimuth of the movable reflector antenna deflects towards the negative half-axis, the azimuth error voltage is positive, and the azimuth-elevation cross-coupling is less than 1 / 5;

[0027] S303. Manipulate the steerable reflector antenna to deflect the antenna elevation so that the elevation of the steerable reflector antenna deflects towards the positive semi-axis, the elevation error voltage is negative, and the azimuth-elevation cross-coupling is less than 1 / 5;

[0028] S304. Manipulate the steerable reflector antenna to deflect the antenna elevation so that the elevation of the steerable reflector antenna deflects towards the negative semi-axis, the elevation error voltage is positive, and the azimuth-elevation cross-coupling is less than 1 / 5.

[0029] The beneficial effects of the present invention are as follows: It has the advantages of short period, low cost, and high efficiency. Description of the Drawings

[0030] Figure 1 It is a flowchart of the phase calibration of the steerable reflector antenna based on a coaxial helicopter UAV.

[0031] Figure 2 It is a schematic diagram of the distance calibration between the steerable reflector antenna and the UAV. Detailed Embodiments

[0032] To make the objectives, technical solutions, and advantages of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below in conjunction with the drawings of the present invention.

[0033] As Figure 1 - Figure 2 shown, a method for phase calibration of a steerable reflector antenna based on a coaxial helicopter UAV includes the following steps:

[0034] S1. The coaxial helicopter UAV carrying a signal generator and a transmitting source antenna takes off to an appropriate position.

[0035] (1) The UAV and the ground steerable reflector antenna are in the same calibration site, and the meteorological conditions, electromagnetic environment conditions, etc. of the calibration site meet the calibration requirements.

[0036] (2) The coaxial helicopter UAV is equipped with a signal generator and a transmitting source antenna.

[0037] The coaxial helicopter UAV is equipped with a payload compartment and a pan-tilt head. A mobile power supply and a signal generator are deployed inside the payload compartment, the mobile power supply powers the signal generator, and a transmitting source antenna is deployed on the pan-tilt head. The signal output by the signal generator is connected to the transmitting source antenna through a feeder.

[0038] (3) The coaxial helicopter UAV flies to an appropriate position, and the appropriate position is divided into the slant range R and the vertical distance H.

[0039] The slant range R: refers to the distance between the transmitting source antenna of the coaxial helicopter UAV and the ground steerable reflector antenna. The slant range R meets the far-field calibration conditions, and the calculation formula is:

[0040] R≥2(D+d)*(D+d) / λ Formula 1

[0041] Where: D is the aperture of the relocatable reflector antenna, unit: m; d is the aperture of the transmitting source antenna, unit: m; λ is the wavelength corresponding to the operating frequency, unit: m.

[0042] Vertical distance H: The vertical distance from the center of the aperture of the transmitting source antenna of the coaxial helicopter UAV to the ground. The vertical distance H meets the far-field calibration condition, and the calculation formula is:

[0043] H≥R*sin(2*θ0.5) Formula 2

[0044] Where: R is the slant range, unit: m; 2*θ0.5 is the half-power beamwidth of the main beam of the relocatable reflector antenna, unit: degree.

[0045] S2, the UAV transmits an appropriate signal, the relocatable reflector antenna points to the UAV transmitting antenna, and receives the transmitted signal of the UAV.

[0046] S201, the transmitting source antenna of the UAV points to the relocatable reflector antenna.

[0047] Before the UAV takes off, according to the position of the ground antenna, calculate the angle at which the transmitting source antenna of the UAV points to the ground relocatable antenna; after the UAV flies to an appropriate position, control the transmitting source antenna of the UAV and point it to the ground relocatable antenna.

[0048] S202, the relocatable reflector antenna points to the transmitting source antenna of the UAV.

[0049] The UAV control terminal can display the longitude, latitude, and altitude of the coaxial helicopter UAV in real time. The servo control software of the ground relocatable reflector antenna can calculate the azimuth angle and elevation angle at which the relocatable reflector antenna points to the coaxial helicopter UAV according to the longitude, latitude, and altitude of the coaxial helicopter UAV, and the relocatable reflector antenna points to the UAV transmitting antenna.

[0050] S203, the UAV signal generator transmits an appropriate signal, the relocatable reflector antenna receives the signal of the UAV, and the relocatable reflector antenna tracks the baseband and locks the transmitted signal of the UAV.

[0051] The signal generator of the coaxial helicopter UAV transmits an appropriate signal through the transmitting antenna, the relocatable reflector antenna captures the signal, and the relocatable reflector antenna tracks the baseband and locks the transmitted signal of the UAV.

[0052] S3, with the cooperation of the relocatable reflector antenna tracking baseband, control the antenna servo software to debug an appropriate antenna phase, so that the relocatable reflector antenna can self-track the transmitted signal of the coaxial helicopter UAV.

[0053] S301, Manipulate the offset of the azimuth of the movable reflector antenna to make the azimuth of the movable reflector antenna shift towards the positive half-axis, the azimuth error voltage is negative, and the azimuth-elevation cross-coupling is less than 1 / 5.

[0054] S302, Manipulate the offset of the azimuth of the movable reflector antenna to make the azimuth of the movable reflector antenna shift towards the negative half-axis, the azimuth error voltage is positive, and the azimuth-elevation cross-coupling is less than 1 / 5.

[0055] S303, Manipulate the offset of the elevation of the movable reflector antenna to make the elevation of the movable reflector antenna shift towards the positive half-axis, the elevation error voltage is negative, and the azimuth-elevation cross-coupling is less than 1 / 5.

[0056] S304, Manipulate the offset of the elevation of the movable reflector antenna to make the elevation of the movable reflector antenna shift towards the negative half-axis, the elevation error voltage is positive, and the azimuth-elevation cross-coupling is less than 1 / 5.

[0057] S4, Save the phase at which the movable reflector antenna can perform self-tracking to the tracking baseband, and this phase is the tracking phase of the movable reflector antenna.

Claims

1. A phase calibration method for a movable reflector antenna based on a rotary wing UAV, characterized in that: The following steps are involved: S1, the helical wing drone carrying the signal generator and the transmitting source antenna takes off to a suitable position; S2, the UAV transmits a suitable signal, the movable reflector antenna receives the UAV's transmission signal, and the movable reflector antenna tracks the baseband and locks the UAV's transmission signal; S3, with the cooperation of the portable reflector antenna tracking baseband, control the antenna servo software and debug the appropriate antenna phase so that the portable reflector antenna can self-track the transmission signal of the rotor UAV; S4, saving the phase of the movable reflector antenna that can be self-tracked to the tracking baseband, and the phase is the tracking phase of the movable reflector antenna.

2. The phase calibration method for a movable reflector antenna based on a rotary wing UAV according to claim 1 is characterized in that: In S1, the UAV and the ground movable reflector antenna are in the same calibration site.

3. The phase calibration method for a movable reflector antenna based on a rotary wing UAV according to claim 1 is characterized in that: In S1, the suitable position includes the slant distance R and the vertical distance H.

4. The phase calibration method for a movable reflector antenna based on a spiral wing UAV according to claim 3 is characterized in that: In S1, the slant distance R meets the far-field calibration condition, and the calculation formula is: R≥2(D+d)*(D+d) / λ Where: D is the aperture of the movable reflector antenna; d is the aperture of the transmitting source antenna; λ is the wavelength corresponding to the operating frequency.

5. The phase calibration method for a movable reflector antenna based on a rotary wing UAV according to claim 3 is characterized in that: In S1, the vertical distance H meets the far-field calibration condition, and the calculation formula is: H≥R*sin(2*θ0.5) Where: R is the slant distance; 2*θ0.5 is the half-power point width of the main beam of the movable reflector antenna.

6. The phase calibration method for a movable reflector antenna based on a rotary wing UAV according to claim 1 is characterized in that: In S1, the helical wing drone is equipped with a signal generator and a transmitting source antenna, and the signal output by the signal generator is connected to the transmitting source antenna.

7. The phase calibration method for a movable reflector antenna based on a rotary wing UAV according to claim 6 is characterized in that: The specific steps of S2 are: S201, the transmitting source antenna of the UAV is directed toward the movable reflector antenna; S202, the movable reflector antenna is directed toward the transmitting source antenna of the UAV; S203, the UAV signal generator transmits a signal, the movable reflective antenna receives the signal from the UAV, and the movable reflective antenna tracks the baseband and locks the transmitting signal of the UAV.

8. The phase calibration method for a movable reflector antenna based on a rotary wing UAV according to claim 1 is characterized in that: The specific steps of S3 are: S301, controlling the movable reflector antenna to deflect the antenna azimuth, so that the azimuth of the movable reflector antenna is offset toward the positive semi-axis, the azimuth error voltage is negative, and the azimuth elevation cross coupling is less than 1 / 5; S302, controlling the movable reflector antenna to deflect the antenna azimuth, so that the azimuth of the movable reflector antenna is offset toward the negative semi-axis, the azimuth error voltage is positive, and the azimuth elevation cross coupling is less than 1 / 5; S303, controlling the movable reflector antenna to deflect the antenna pitch, so that the movable reflector antenna pitch is offset to the positive semi-axis, the pitch error voltage is negative, and the azimuth-elevation cross coupling is less than 1 / 5; S304, controlling the movable reflector antenna to deflect the antenna pitch, so that the movable reflector antenna pitch is offset to the negative semi-axis, the pitch error voltage is positive, and the azimuth-elevation cross coupling is less than 1 / 5.

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