JPS62263484A - Precision approach radar - Google Patents

Abstract

PURPOSE:To enhance the safety of an airplane, by providing a radar signal transmitting part for transmitting radar information to the airplane to precision approach radar. CONSTITUTION:The synchronizer 16 of PAR1 sends trigger (c) to a transmitting part 13, a receiving part 4 and an indication part 15, and an angle signal generating part 7 generates an angle signal (b) showing the azimuths and high and low angles of antennae 11, 12. PAR1 outputs the video signal (a) from the receiving part 14, the angle signal (b) from the generating part 17 and the trigger C from the synchronizer 16 to a rader signal transmitting part 2. A target detection part 3 receives said signals to detect the angle signal of an airplane and, in an operation part 4, the difference between said signal and the angle signal operated from the distance data of a preset grindscope, a course line and a PAR-loading point is calculated and an output signal is emitted to the airplane 58 from antenna to be displayed on a meter in the side of the airplane 58. Therefore, the airplane 58 lands while a pilot monitors the display device on the own airplane and confirms the position of the own airplane without radio wave comunication between a controller and the pilot and, as a result, the position of the airplane can be monitored on both of the ground and the airplane and safety is further enhanced.

Description

[Detailed description of the invention] [Industrial application field] The present invention relates to a precision approach radar for an air traffic control radar.

[Conventional technology]

Precision Approach Radar, or PAR (Precisi
on^pproach Radar) is used to detect three-dimensional information (azimuth, altitude, distance) of an aircraft approaching the runway and safely guide the aircraft to the landing point.

The basic system diagram of PAR is shown in Fig. 2. PAR has two antennas 11 and 12 for azimuth and altitude, and a pulse modulated transmission signal with a frequency of 9000 MHz band generated by a transmitter 13 is transmitted to the antenna 11. ．． ．． It radiates alternately from 12.

The reflected signal from the aircraft is sent from the antenna 11.12 to the receiver 1.
4, and after being amplified and detected by the receiving section 14, the instruction section 1
5 and displayed on the supercope.

FIGS. 3(a) and 3(b) show the antenna 11 shown in FIG.
Installation location and cover of PAR station building 50 equipped with 12 etc.! i5
FIG. 2.53 is a plan view and a side view. PARl
The station building 50 is installed next to the runway 51, and the station building 50 is installed next to the runway 51, and
> has a coverage area 52.53 of about 20° in the horizontal plane, and about 7° in the vertical plane as shown in FIG. 3(b).

In addition, the detection distance is approximately 10 N M (na
In the figure, 54 is a landing point, 56 is a course line, 57 is a glideslope, and 58 is an aircraft.

FIG. 4 shows how the aircraft 58 is guided by PARl. The controller reports the position of the aircraft 58 to the pilot via five anti-aircraft radios while monitoring the scope of the instruction unit 15, and follows the preset descent route (glide slope 57).
and the course line 56) so that the aircraft [58] passes over the course line 56).

If aviation a! If the 158 deviates from its descent path, the controller will notify the pilot and the pilot will correct the trajectory. The controller also reports the distance from the landing point 54 to the aircraft 58 to the pilot.

[Problem that the invention seeks to solve]

In the conventional landing guidance control using PAR described above, the controller notifies the pilot via anti-aircraft radio of the aircraft's deviation from the descent path, so the pilot can directly visually confirm the position of the aircraft. It was impossible.

Another disadvantage is that even if the PAR is operating normally, it cannot guide the aircraft if the radio is malfunctioning.

[Means for solving problems]

The precision approach radar device of the present invention is characterized in that it includes a radar signal transmission section that transmits radar information to an aircraft.

〔Example〕

Next, the present invention will be explained with reference to the drawings.

FIG. 1 is a block diagram showing one embodiment of the present invention. In the figure, PARI is similar to that shown in Figure 2,
The synchronized nine 16 and the angle signal generator 17 are also shown in more detail in FIG. The synchronizer 16 includes the transmitter 13,
A trigger C is sent to the receiving section 14 and the instruction section 15, and the angle signal generating section 17 generates an angle signal indicating the direction and height angle of the antenna 11, 12. From PARI, the video signal a from the receiving section 14, the angle signal S from the angle generating section 17, and the trigger C from the synchronizer 16 are outputted to the radar signal transmitting section 2 according to the present invention. video signal a
For this purpose, an MTI video signal from which ground clutter has been removed is used to easily extract the signal from the aircraft.

The target detection section 3 in the radar signal transmission section 2 receives the video signal a.
It extracts the aircraft signal from among the signals and outputs only the angle signal at the timing when the aircraft signal exists. Also, the distance is determined from the time difference between the trigger C and the aircraft signal, encoded, and output. A block diagram of the target detection section 3 is shown in FIG. 5, and a timing chart is shown in FIG. 6. In the target detection section 3 of FIG. 5, the video signal a and the angle signal as well as the azimuth and elevation signals from the antennas 11 and 12 are input in a time-division manner, so that the same circuit can be used.

In FIG. 5, a comparator 31 compares the video signal a with a certain threshold level to detect the aircraft signal d, and a counter 32 detects the number of clock signals from the clock generator 33 from the trigger C to the aircraft signal d. The code generator 34 converts the output of the counter 32 into a distance signal f
and output it. The gate generator 36 receives the aircraft signal d, sends the gate signal e to the gate 36, and passes the current angle signal to form the angle signal g.

The angle signal g of the aircraft from the target detection unit 3 is sent to the calculation unit 4, where the angle signal is calculated from data on the glide slope 57, the course line 56, and the distance to the PAR-landing point 54 set in advance. The difference is required. A block diagram of the calculation unit 4 is shown in FIG. 7. A memory 21 in FIG. 7 is a memory for storing data such as the glide slope 57. The angle calculator 22 calculates the angles of the bride slope 57 and the course line 56 for each distance based on the data from the memory 21 and outputs them to the memory 23. This calculation is only an initial calculation and is not necessary as long as the input data such as the glide slope 57 does not change.

The angle data stored in the memory 23 is read out by the distance signal f input from the target detection unit 3, and
The difference between the angle signal g and the aircraft angle signal g is determined here. The obtained difference signal and distance signal g are input to the synthesizer 25, combined, and output from the calculation section 4.

The signal from the arithmetic unit 4 is converted, modulated, and amplified by the transmitting unit 5 into a signal suitable for transmission to an aircraft, and then radiated to the upstream aircraft 58 from the antenna 6. Aircraft 5811- receives these signals, amplifies and demodulates them, and displays them on the meters.

For example, in the radar signal transmission section 2, the deviation from the descent route,
The distance is digitized and transmitted to Aviation 1!158. On the aircraft 58 side, the digital signal is converted to analog, and the deviation is I L S (Instrument Landing
5yste■) is displayed on the meter. Also, DM for distance
E (mouth 1stance MeasuringEquip
ment) will be displayed on the meter.

〔Effect of the invention〕

As explained above, the present invention is equipped with a radar signal transmission section for directly transmitting PAR three-dimensional information to the aircraft, so that the pilot can receive information on the aircraft without relying on radio communication between the controller and the pilot. You can land while checking the position of your aircraft by monitoring the display.

The present invention makes it possible to monitor the position of an aircraft both on-board and on the ground, thereby further improving safety.

[Brief explanation of drawings]

Fig. 1 is a block diagram of an embodiment of the present invention, Fig. 2 is a basic block diagram of a conventional PAR, and Fig. 3 (a> and (b)
) are a plan view and a side view showing the installation location and coverage area of PAR, respectively, Figure 4 is an explanatory diagram showing the conventional control by PAR, and Figures 5 and 6 are the target detection shown in Figure 1, respectively. Block Diagram and Timing Chart of Unit 3, FIG. 7 is a block diagram of the arithmetic unit 4 shown in FIG. 1. 1...PAR12...Radar signal transmission section, 3...
1 Drift detection section, 4... Calculation section, 5... Transmission section, 6...
- Antenna, 11... Azimuth antenna, 12... Altitude antenna, 13... Transmitting section, 14... Receiving section, 15...
Measurement section, 16... synchronizer, 17... angle signal generation section.゛148. ．． Class, 2', -1' 27th (Ri訃3 dissection!; ferti

Claims (1)

[Claims] A precision approach radar device comprising a radar signal transmission unit that transmits radar information to an aircraft.