JP2850528B2 - Radio emission control device - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION [Industrial Application Field] The present invention is used for a radio wave radiation control device of an active phased array radar device. In particular, a radio wave emission control device that emits radio waves efficiently by changing the radio wave emission time interval according to the correlation with the flight plan of the aircraft in flight and the magnitude of the turning angular velocity of the aircraft, and improves the tracking ability of tracking [Summary] The present invention relates to a radio wave emission control device, which performs a correlation determination of position information and speed information with a flight plan for a flying aircraft, and, if there is a correlation, an estimated azimuth based on the position information. Radio wave emission priorities and set a longer radio wave emission time interval.If there is no correlation, detect the turning angular velocity of the aircraft, determine the predicted azimuth and radio wave emission priority according to the detected turning angular velocity, and By setting the time interval optimally, radio waves can be emitted efficiently and tracking ability can be improved, enabling accurate air traffic control. Things.

[Conventional technology]

FIG. 3 is a diagram showing a tracking operation of a conventional radio wave emission control device.

Conventionally, the radar apparatus has not performed the radio wave emission time interval control according to the turning of the aircraft, but has performed the radio wave emission control at predetermined time intervals based on the flight plan of the aircraft.

[Problems to be solved by the invention]

However, in such a conventional radio wave emission control device, the radio wave emission time interval is set to a predetermined interval regardless of the type of aircraft and the movement of the turning flight. Because the main flight is a straight-line flight, extra radio waves are emitted, and sufficient radio emissions are not obtained for aircraft that make sharp turns, making it difficult to perform accurate air traffic control due to increased tracking loss. There were drawbacks.

SUMMARY OF THE INVENTION An object of the present invention is to solve the above-mentioned drawbacks, and an object of the present invention is to provide a radio wave emission control device capable of emitting radio waves efficiently, improving tracking ability, and performing accurate air traffic control.

[Means for solving the problem]

The present invention provides a tracking processing unit that inputs position data of an aircraft in flight from an active phased array radar device and outputs position information and speed information of the aircraft, and outputs beam scanning data based on the input predicted azimuth and radio wave emission time. In a radio wave radiation control device including a beam scanning means provided to the active phased array radar device, a correlation between position information and speed information from the tracking processing unit and position information and speed information of the flight plan of the aircraft is determined. A correlation unit that outputs the position information and the radio wave emission priority from the tracking processing unit when there is a correlation, and outputs the position information from the tracking processing unit when there is no correlation.
A turning angular velocity detecting section that calculates and outputs a turning angular velocity based on the position information from the correlating section, and the predicted azimuth based on the position information and the radio wave emission priority from the correlating section or the position information from the turning angular velocity detecting section. And a radio wave emission priority control unit that determines and outputs a radio wave emission time.

Further, the present invention includes a flight plan buffer for storing position information and speed information of flight plans of a plurality of aircraft, and the correlating unit calculates the position information and speed information of the flight plan of the corresponding aircraft from the contents of the flight plan buffer. May be included.

[Action]

The correlation unit determines a correlation between the position information and the speed information from the tracking processing unit and the position information and the speed information of the flight plan of the aircraft, and outputs the position information and the radio wave emission priority from the tracking processing unit when there is a correlation. Then, when there is no correlation, the position information from the tracking processing unit is output. The turning angular velocity detector calculates and outputs the turning angular velocity based on the position information from the correlator. The radio wave emission priority control section determines a predicted azimuth and a radio wave emission time based on the position information from the correlation section and the radio wave emission priority or the position information from the turning angular velocity detection section, and outputs them to the beam traveling means.

Further, the flight plan buffer stores the position information and speed information of the flight plans of a plurality of aircraft, and the correlator reads out the position information and speed information of the flight plan of the corresponding aircraft from the contents of the flight plan buffer and performs correlation determination.

As described above, efficient radio wave emission can be performed, and tracking ability can be improved, and accurate air traffic control can be performed.

〔Example〕

Embodiments of the present invention will be described with reference to the drawings. FIG. 1 is a block diagram of a radio wave emission control device according to an embodiment of the present invention. In FIG. 1, a radio wave radiation control device is a radar device 1 as an active phased array radar device.
Tracking processing unit 3 for inputting the position data (Ri, θi) of the aircraft in flight from, and outputting the position information and speed information of the aircraft as tracking information ( _xSi , _ySi , _Si , _Si )
A radar hit driver 7, an angle generator 8, and a beam scanner 9 as beam scanning means for providing beam scanning data to the radar device 1 based on the input predicted orientation (θ _pi ′) and radio wave emission time (t). And a timing control section that supplies a clock signal to each section.

Here, the features of the present invention include the tracking information ( _xSi , _ySi , _Si , _Si ) from the tracking processing unit 3 and the flight plan data ( _xfi , y _fi , _fi , _fi ) are determined, and if there is a correlation, the position information (x _Si , y _Si ) and the radio wave emission priority (P _L ) from the tracking processing unit 3 are output. position information from the tracking processing unit 3 if (x _Si, y _Si) and the correlation unit 4 that outputs, calculates the position information from the correlator 4 (x _Si, y _Si) turning angular velocity based on the (omega ₀₎ a slewing angular velocity detecting section 5 for outputting Te, position information from the correlator 4 (x _Si, y _Si) and radio emission priority (P _L) and the position information from the turning angular velocity detection unit 5 (x _Si, y _Si) and the prediction direction (θ _pi ') and radio emission priority control unit 6 which radio emission time (t) determined by the output based on Lies in the fact that with.

In addition, flight plan data (x
flight plan buffer 2 for storing _fi , y _fi , _fi , _fi )
The correlating unit 4 calculates the flight plan data (x _fi , y _fi ,
_fi , _fi ).

The operation of the radio wave emission control device having such a configuration will be described. FIG. 2 is a diagram showing a tracking operation of the radio wave emission control device of the present invention.

In FIG. 1 and FIG. 2, position data (R _i , θ _i ) obtained from the radar device 1 is input to the tracking processing unit 3. The tracking processing unit 3 performs tracking based on the position data (R _i , θ _i ), and outputs tracking information (x _Si , y _Si , _Si , _Si ) as a tracking processing result to the correlation unit 4.

The correlation unit 4 inputs the flight plan data (x _fi , y _fi , _fi , _fi ) from the contents of the flight plan buffer 2 and the tracking information (x _si , y _si , _si , _si ) from the tracking processing unit 3 and inputs the position and Performs speed correlation determination.

If the correlation unit 4 determines that there is a correlation, the radio wave radiation priority control unit 6 outputs a radio wave radiation priority order (P _L ). If the correlation unit 4 determines that there is no correlation, the position data (x _si , y _si ) is output to the turning angular velocity detection unit 5.

The turning angular velocity detector 5 outputs the current position data (x _si ,
y _si ), the turning radius (R ₀ ) and the turning angular velocity (ω ₀ ) based on the previous position data (x _si-1 , y _Si-1 ) and the position data before (x _si-2 , y _si-2 ). And outputs the turning angular velocity (ω ₀ ) to the radio wave emission priority control unit 6.

Here, the calculation of the turning radius (R ₀ ) _{However, X 0 = {2 · (} x 1 · 1 + y 1 · 1) - 1 · (x 2 · 2 + y 2 · 2)} / 2 · (1 · 2 - 2 · 1) Y 0 = {2 · _{(x 1 · 1 + y 1} · 1) - 1 · (x 2 · 2 + y 2 · 2)} / 2 · (2 · 1 - 1 · 2) x 1 = X si-2 + X si-1, 1 = X _si-2 -X _si-1 x ₂ = X _si-1 + X _si , ₂ = X _si-1 -X _si y ₁ = Y _si-2 + Y _si-1 , ₁ = Y _si-2 -Y _{si- 1} y ₂ = Y _si-1 + Y _si , ₂ = Y _si-1 −Y _{si Further} , the calculation of the turning angular velocity (ω ₀ ) is as follows. T ₀ : {acquisition time of position data (X _si , X _si )} − {acquisition time of position data (X _si−1 , Y _si−1 )}.

Radio emission priority control section 6, the relevant next by radio emission priority (P _L) or slewing angular velocity from the turning angular velocity detection unit 5 (omega ₀₎ radio emission priority corresponding to from correlation section 4 (P _L) The radio wave emission time (t) with respect to the aircraft and the predicted azimuth (θ _p ′) of the aircraft after the time (t) are output to the calculated radar heat drive unit 7.

The radar hit driver 7 outputs the predicted azimuth (θ _pi ′) to the angle generator 8 after a time (t).

The angle generating unit 8 outputs to the beam traveling unit 9 azimuth data (θ) periodically generated from the north based on the clock signal from the normal timing control unit 10, and outputs the predicted azimuth (θ _pi) from the radar hit driving unit 7. ′) Is input, the azimuth data (θ) is stopped, and the predicted azimuth (θ _pi ′) is output to the beam scanning unit 9. When this operation is completed, the stopped azimuth data (θ) is output to the beam scanning unit 9 again.

The beam scanning unit 9 outputs beam scanning data to the radar device 1 and performs beam scanning control.

The timing controller 10 outputs a clock signal to the angle generator 8 and controls the processing timing of each unit.

〔The invention's effect〕

As described above, the present invention has an excellent effect that radio waves can be emitted efficiently, tracking ability can be improved, and accurate air traffic control can be performed.

[Brief description of the drawings]

FIG. 1 is a block diagram of a radio wave emission control device according to an embodiment of the present invention. FIG. 2 is a diagram showing a tracking operation of the radio wave emission control device of the present invention. FIG. 3 is a diagram showing a tracking operation of a conventional radio wave emission control device. DESCRIPTION OF SYMBOLS 1 ... Radar apparatus, 2 ... Flight plan buffer, 3 ... Tracking processing part, 4 ... Correlation part, 5 ... Turning angular velocity detection part, 6
... radio wave emission priority control unit, 7 ... radar hit drive unit,
8 ... Angle generating unit, 9 ... Beam scanning unit, 10 ... Timing control unit.

──────────────────────────────────────────────────続 き Continued on the front page (58) Field surveyed (Int. Cl. ⁶ , DB name) G01S 7/02-7/42 G01S 13/00-13/95

Claims (2)

(57) [Claims] 1. A tracking processing unit for inputting position data of an aircraft in flight from an active phased array radar device and outputting position information and speed information of the aircraft, and beam scanning data based on the input predicted azimuth and radio wave emission time. And a beam scanning means for providing the active phased array radar device with a beam scanning means for determining a correlation between the position information and the speed information from the tracking processing unit and the position information and the speed information of the flight plan of the aircraft. A correlation unit that outputs the position information and the radio wave emission priority from the tracking processing unit when there is a correlation, and outputs the position information from the tracking processing unit when there is no correlation; and a position from the correlation unit. A turning angular velocity detector that calculates and outputs a turning angular velocity based on the information; A radio wave radiation control unit for determining and outputting the predicted azimuth and radio wave radiation time based on the firing priority or the position information from the turning angular velocity detection unit. 2. A flight plan buffer for storing position information and speed information of flight plans of a plurality of aircrafts, wherein the correlating unit obtains position information and speed information of flight plans of the corresponding aircraft from the contents of the flight plan buffers. The radio wave emission control device according to claim 1, further comprising a reading unit.