JPH04204191A - Precision approach radar apparatus - Google Patents

Abstract

PURPOSE:To achieve a higher detection probability of an aircraft by enabling the varying of an interval of a power output of a transmitter to irradiate the aircraft to be guided with a large amount of energy of a transmission power. CONSTITUTION:A trigger generator 2-2 generates a trigger signal with a cycle N+A longer by a value A than a fixed cycle Npps and a trigger generator 2-3 generates a trigger signal with a cycle N-B shorter by a value B than the value to be inputted into a switch 2-4 separately. Then, the switch 2-4 selects and outputs one of the two inputs according to a gate signal from a gate generator 1. With manual operation of a servo mechanism, a switch 2-5 operated to select an output of the switch 2-4 and a precision approach radar PAR works at a variable cycle -- long cycle (N+A) and a short cycle (N-B). As a result, a transmitter 3 outputs a power at a short cycle within a range near an area where an aircraft to be guided exists and the number of hits to the aircraft increases to irradiate it with a large amount of energy.

Description

Detailed Description of the Invention (Field of Industrial Application) The present invention is directed to a precision approach radar system (PAR), which is a ground device for safely landing an aircraft.
on Approach Radar).

(Prior Art) FIG. 4 shows a typical coverage area of PAR. The coverage area of the PAR direction and height is determined by the range scanned by the direction antenna and the height antenna. For example, in the illustrated example, the azimuth antenna scans a range of 20 degrees in the azimuth direction with a fan beam having a horizontal width of about 0.8 degrees and a vertical width of about 2 degrees. In addition, the height antenna scans a range of 7" in the height direction using a fan beam with a vertical width of approximately 0.5° and a horizontal width of approximately 3°.The azimuth antenna is then moved by a servo mechanism to scan a range of 7" in the height direction. It can be tilted, and the height antenna can be tilted 20'' in the azimuth direction.

In PAR, a transmitter outputs constant power to both antennas at regular intervals to radiate it into space, and both antennas are driven in a fixed order to repeatedly scan the coverage area. If there is a reflected wave from the aircraft during this time, it is displayed as radar video on the display screen of the indicating device and notified to the controller.

Then, when the controller manually operates the servo mechanism and sets the altitude antenna at a certain angle in the azimuth direction, and also sets the azimuth antenna at a certain angle in the altitude direction, both antennas will move within their respective scanning ranges at the specified angle. scan.

If an aircraft is located at the intersection of the scanning directions of both antennas, that aircraft can be captured with maximum sensitivity.

In other words, the controller continues to monitor the aircraft's position by manually operating the servo mechanism of the azimuth antenna and altitude antenna so that the radar video signal of the aircraft is displayed in the optimal condition on the display screen of the indicating device. The system communicates with the pilot and guides the aircraft to match the course line and glide path.

(Problem to be Solved by the Invention) In the conventional PAR described above, the antenna can be operated by a servo mechanism so that the beam is directed to the position where the aircraft is, but the power from the transmitter is always transmitted into the air at a constant cycle. Because it is radiated, energy is dispersed even in directions where the aircraft is not present.

Furthermore, there is a problem in that radiation to the ground surface where no aircraft is present causes many reflections from the ground surface, resulting in the reception of unnecessary signals.

The present invention has been made in view of such problems, and an object thereof is to provide a precision approach radar device equipped with a means for making the interval between transmitter power outputs variable in accordance with the beam direction of the antenna. It's about doing.

(Means for Solving the Problems) In order to achieve the above object, the precision approach radar device of the present invention has the following configuration.

That is, the precision approach radar device of the first invention includes means for receiving angle signals from the antennas (azimuth antenna and height antenna) and generating a gate signal specifying a predetermined angle range within the scanning range of the antenna; means for generating a first trigger signal; upon receiving the gate signal, the period is longer than the fixed period N outside the predetermined angular range, and the period is shorter than the fixed period N within the predetermined angular range; The present invention is characterized by comprising: means for generating a variable period trigger signal; and means for switching between the first trigger signal and the variable period trigger signal and outputting the switched signal to a transmitter or the like.

The precision approach radar device of the second invention further includes a gate generator that receives angle signals from the antennas (azimuth antenna and elevation antenna) and generates a gate signal that designates a predetermined angle range within the scanning range of the antenna; a first trigger generator that generates a first trigger signal with a period N; a second trigger generator that generates a second trigger signal with a period longer than the certain period N; a second trigger signal with a period shorter than the certain period N; a third trigger generator that generates three trigger signals; upon receiving the gate signal, selects the output of the second trigger generator outside the predetermined angle range, and selects the output of the third trigger generator within the predetermined angle range; A first switching device that selects an output: A second switching device that selects and outputs either the output of the first trigger generator or the output of the first switching device by external operation; and: Sending the output of the second switching device. It is characterized by being equipped with a distributor for distributing to machines, etc.;

(Function) Next, the function of the precision approach radar device of the present invention configured as described above will be explained.

When an aircraft is detected within the coverage area, the antenna scans in the azimuth and elevation directions at an angle specified by the deputy's manual operation. Then, in the present invention, the period of the power output of the transmitter is divided into two periods from the constant period N, a long period outside the predetermined area near the aircraft's location, and a short period within the predetermined area near the aircraft's location. changed to one cycle.

As a result, a large amount of transmitted power energy can be irradiated to the aircraft, increasing the probability of detecting the aircraft.

Furthermore, the energy of the transmitted power can be reduced to areas other than the vicinity of the aircraft presence area, and reflections from the ground surface, buildings, etc. are reduced.

(Example) Embodiments of the present invention will be described below with reference to the drawings.

FIG. 1 shows a precision approach radar system according to an embodiment of the present invention. As shown in FIG. 1, in the present invention, a gate generator 1 is newly installed, and some functions are added to a synchronizing signal generator 2.

As shown in the figure, the transmitter 3, receiver 4, indicating device 5, etc. all operate at a constant timing according to the same trigger signal distributed and supplied from the distributor 2-6 of the synchronization signal generator 2.

Conventionally, in the synchronization signal generator 2, the output of the trigger generator 2-1, which generates a trigger signal with a constant cycle of N pps, is directly input to the distributor 2-6. As a result, conventionally, the power radiated into space from the transmitter 3 has a constant period N pps
The power energy was radiated evenly over a 20° range in direction and a 7″ range in elevation.

The synchronization signal generator 2 of this embodiment includes two trigger generators (2-2, 2-3) and two switches (2-4, 2-5).
) is added. The trigger generator 2-2 has a constant period N
A trigger signal with a period N+AI)I)S that is longer than pps by a value A is generated. This becomes one input of switch 2-4. Further, the trigger generator 2-3 generates a trigger signal with a cycle NB shorter than the constant cycle N by a value B.

This becomes the other input of switch 2-4.

The switch 2-4 performs a switching operation according to a gate signal from the gate generator 1, and selectively outputs one of the two outputs.

One input of the switch 2-5 is the output of the trigger generator 2-1, and the other input is the output of the switch 2-4, and the switch 2-5 performs a switching operation according to the manual operation of the air traffic controller, and switches one of the two manually. It is selected and output to the distributor 2-6.

That is, this switch 2-5 is operated to select the output of the trigger generator 2-1 before manual operation of the servo mechanism is started. As a result, the PAR operates at a constant cycle N pps as in the conventional case. Then, when starting manual operation of the servo mechanism, switch 2-5 is operated to select the output of switch 2-4. As a result, the corresponding PAR has a long period (N+A) and a short period (N-
It will operate at the variable cycle of B).

Next, the angle signal θ (AZ/EL) input from the angle signal generator 6 to the gate generator 1 changes within a range of 20 degrees in direction (AZ) and 76 degrees in elevation in conjunction with the mechanical movement of the antenna. do. Correspondingly, the display screen of the pointing device 5 displays elevation and direction as shown in FIG.

Figure 3 is an example of a display when an air traffic controller manually operates a servo mechanism to guide an aircraft. EL angle range), and a predetermined angle range (AZ angle range) across the course line are respectively designated and input to the gate generator 1 in the azimuth.

FIG. 2 shows the generation of a gate signal in the case of sub-pressure, and the gate generator 1 generates a level of "1" within the scanning range of the antenna from the angle signal and the angle range designation signal, for example, within the designated angle range. , generates a gate signal that becomes 0''' level outside the specified angle range.

The switch 2-4 selects the long period (N+A) trigger signal which is the output of the trigger generator 2-3 when the gate signal is "01 level", and selects the trigger signal of the long period (N+A) which is the output of the trigger generator 2-3 when the gate signal is "1" level. Select the short period (N-B) trigger signal which is the output of 2-2.

As a result, in a predetermined angular range in the vicinity of the aircraft to be guided, the transmitter 3 outputs power in short cycles (N-B). This increases the number of hits directed at the aircraft and irradiates the aircraft with more energy. Conversely, in an uncontrolled angular range, the transmitter 3 outputs power in a long period (N+A).

This reduces energy dispersion.

(Effects of the Invention) As explained above, according to the precision approach radar device of the present invention, since a means for making the power output cycle of the transmitter variable is provided, the energy of the transmitted power is applied to the aircraft to be guided. can irradiate a large amount of light, which has the effect of increasing the probability of aircraft detection. Furthermore, the energy of the transmitted power can be reduced by lengthening the transmission interval to areas other than the vicinity of the position where the aircraft to be guided exists, which has the effect of reducing reflections from the ground surface, buildings, etc.

[Brief explanation of the drawing]

FIG. 1 is a system diagram showing an embodiment of the present invention, FIG. 2 is a diagram showing the explanation for generating gates in terms of height, and FIG. 3 is a short portion of the transmission power interval on the display screen of the indicating device, FIG. 4 is a diagram showing an example of a long portion, and is a diagram showing the coverage area of PAR. 1... Gate generator, 2... Synchronization signal generator, 2-1.2-2.2-3... Trigger generator, 2-4.2- 5...Switch, 2
-6...Distributor, 3...Transmitter,
4...Receiver, 5...Instruction device,
6...Angle signal generator. Agent: Yoshihiro Yahata, Patent Attorney, Gate Registration No. 2, Nine Shells, Sei 1]] Insertion Radar (βAR) Trap Curse Figure 4

Claims (2)

[Claims] (1) means for receiving the angle signals of the antennas (azimuth antenna and height antenna) and generating a gate signal specifying a predetermined angle range within the scanning range of the antenna;
means for generating a trigger signal; a variable period trigger that receives the gate signal and has a cycle longer than the constant cycle N outside the predetermined angular range and shorter than the constant cycle N within the predetermined angular range; A precision measurement approach radar device comprising: means for generating a signal; and means for switching between the first trigger signal and the period variable trigger signal and outputting the switched signal to a transmitter or the like. (2) a gate generator that receives angle signals from the antennas (azimuth antenna and height antenna) and generates a gate signal specifying a predetermined angle range within the scanning range of the antenna; generates a first trigger signal with a constant period N; a first trigger generator; a second trigger generator that generates a second trigger signal with a cycle longer than the constant cycle N; and a third trigger generator that generates a third trigger signal with a cycle shorter than the constant cycle N. a first switch that receives the gate signal and selects the output of the second trigger generator outside the predetermined angle range, and selects the output of the third trigger generator within the predetermined angle range; The output of the first trigger generator and the first
A precision approach radar device comprising: a second switch that selectively outputs one of the outputs of the switch; and a distributor that distributes the output of the second switch to a transmitter or the like.