JP2743626B2 - Azimuth / distance measuring device - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an azimuth / distance measuring device (Takan device), which is a navigation assistance device.

[0002]

2. Description of the Related Art As is well known, a heading / distance measuring device (Takan device), which is a navigation assistance device, comprises an interrogator mounted on an aircraft and a transponder mounted on the ground. As shown in FIG. 3, the interrogator 31 includes a pulse generator 32, a transmitter 3, a receiver 5, an antenna 4, a signal processor 36, and a display indicator 7, and the transponder 41 includes an antenna 1 as shown in FIG.
2. A receiver 13, a transmitter 16, a signal processor 44, and a pulse generator 15. The aircraft (interrogator 31) issues an interrogation pulse to obtain azimuth and distance information from the ground station (transponder 41). , The distance measurement and the azimuth measurement are performed (signal processor 36), and the result is displayed on the display indicator 7. The outline of the distance measurement and the azimuth measurement will be described below with reference to FIGS.

[0003] The transponder 41 generates and transmits various pulses as shown in FIG. First, distance measurement is performed as follows. This is similar to the principle of radar ranging. That is, the transponder 41 is connected to the interrogator 31.
A response pulse is transmitted in response to the interrogator pulse from the interrogator 31. Since a constant value of 50 μs is given as the processing time of the transponder 41, as shown in FIG. Calculate the time until reception, and from that time a fixed value (50 μs)
The distance is measured by subtracting.

[0006] Next, the azimuth measurement is performed using only the radio wave emitted from the ground station. That is, a north azimuth reference pulse (NRB), a 40 degree azimuth reference pulse (ARB), and a random pulse generated by the pulse generator 15 of the transponder 41 are emitted from the antenna 12 through the signal processor 44 and the transmitter 16. At this time, as shown in FIG. 6 and FIG. 7, spatial modulation is performed by a combined wave of 15 Hz and 135 Hz. This modulation pattern and the north reference pulse (NR
The positional relationship between B) and the 40-degree azimuth reference pulse (ARB) is predetermined. That is, the north reference pulse (NR
B) is fired when the maximum value of the spatial modulation pattern is facing east. Also, the 40-degree azimuth reference pulse (ARB) is
It is fired eight times per one revolution of the antenna every 40 electrical degrees after the north azimuth reference pulse (NRB) fired. Therefore, the azimuth can be known from the positional relationship between the spatial modulation pattern and the north azimuth reference pulse (NRB) and the 40-degree azimuth reference pulse (ARB). Specifically, this is performed as shown in FIGS. Note that the 40-degree azimuth reference pulse (ARB) and the 135 Hz modulated wave are the same as the north azimuth reference pulse (NRB) and 1
It is used to improve the azimuth accuracy for a 5 Hz modulated wave by 9 times. This is the same as the function of the vernier in the caliper.

FIGS. 8 and 9 show the reception waveform and signal processing of an aircraft in the east (this position is west from the aircraft, ie, at a position of 270 °). The interrogator 31 selects a north reference pulse (NRB) from the signal of the reception waveform shown in FIG.
Only 15 Hz is extracted from the 35 Hz synthetic wave using a filter. Then, the selected north direction reference pulse (NR
B) A sector is specified every 40 ° with the electrical angle from the negative to the positive zero crossing point of the signal and the 15 Hz signal as the coarse azimuth. Next, similarly, a 40-degree azimuth reference pulse (ARB) signal and a 135 Hz signal are selected from the signal of the reception waveform shown in FIG.
The electrical angle from the negative to the positive zero cross point of the 5 Hz signal is determined, and the azimuth is determined as shown in FIG.

[0006]

As described above, the conventional azimuth / distance measuring device is configured to provide the azimuth and the distance information from the ground station to the aircraft. There is no means to know the direction. Therefore, when checking the reception status of the interrogator at the time of flight inspection of the transponder, it must be checked wirelessly, which is troublesome .
There is a problem that the inspection problem on the transponder side for the notification of the unlock indicating that the comprehension of the azimuth and the distance has become impossible cannot be promptly processed.

An object of the present invention is to provide an azimuth / distance measuring device provided with a means for knowing the position and azimuth of an aircraft at a ground station.

[0008]

In order to achieve the above object, the azimuth / distance measuring device of the present invention has the following configuration. That is, the azimuth / distance measuring device of the present invention is a azimuth / distance measuring device composed of an interrogator mounted on an aircraft and a transponder installed on the ground; a specific signal transmitted from the transponder to the interrogator. Means for transmitting a response in the form of a specific response pulse train composed of a plurality of pulses having a predetermined interval to the north azimuth reference pulse, wherein the transponder receives the response transmission of the interrogator as an object, and wherein the double of the particular pulse train including the received signal output of the receiver; a receiver for receiving and processing the specific response pulse train orientations, captured in a plurality of antenna and the plurality of antenna arrays form that allows determining the
Formed so that aircraft orientation can be determined by a number of antennas
The direction of the aircraft is calculated based on the intensity of the reception level corresponding to the intensity of each directional direction, the quality of the reception state is determined, and the aircraft is determined based on the time from transmission to reception of the north direction reference pulse. A data processor for calculating and outputting the distance; an indicator for displaying the azimuth, the distance, and the reception state output by the data processor;

[0009]

Next, the operation of the azimuth / distance measuring device of the present invention configured as described above will be described. In the present invention, the transponder converts the response signal indicating the reception state from the interrogator into a three-pulse train formed by three pulses as a specific pulse train transmitted based on the reception of the north azimuth reference pulse as the specific signal transmitted by the transponder. receiving, be those determined based bearing and distance of the aircraft, the receiving state to the time between the reception level and the transmission and reception of a particular pulse train
The intensity of each directional direction formed by multiple antennas
The azimuth of the aircraft is calculated based on the reception level corresponding to (directional characteristics) , and the distance to the aircraft is calculated and displayed based on the time between transmission and reception. Therefore, the direction and distance of the aircraft can be known at the ground station , and three-pulse consecutive reception
Check the reception status of the interrogator via the status
it can. As a result, in the flight inspection of the ground station, problem handling such as unlocking can be quickly determined. Further, the safety as a navigation assistance system can be further enhanced.

[0010]

Embodiments of the present invention will be described below with reference to the drawings. FIG. 1 shows an azimuth / distance measuring device according to an embodiment of the present invention. Note that the same components as those in the related art are denoted by the same reference numerals. In the present invention, the interrogator 1 has the same components as the conventional one, but adds a small function to the pulse generator 2 and the signal processor 6, and the transponder 11 can determine the orientation of the aircraft. Array format
In this embodiment, a plurality of antennas (1 to n) 17 in the form of a cylindrical array similar to the TACAN antenna , a receiver 18, a data processor 19, and an indicator 20 are additionally provided. Control signal from processor 14 to data processor 19 (receiver gate)
b is output. Hereinafter, description will be made with reference to FIG.

In the transponder 11, as in the prior art,
Pulse generator 15 is the north azimuth reference pulse, 40 degree azimuth reference
A transmission pulse including various pulses including a random pulse or a response pulse in addition to a pulse is generated (FIG. 2A).
The signal is transmitted from the antenna 12 via the signal processor 14 and the transmitter 16. At this time, the signal processor 14 synchronizes with the north azimuth reference (NRB) pulse to set the receiver gate b (FIG. 2).
(B)) is formed and output to the data processor 19.

The interrogator 1 decodes the north azimuth reference (NRB) pulse in the signal received and input by the signal processor 6 via the antenna 4 and the receiver 5, and decodes the reception level.
To determine the quality of the reception state based on the Le, especially accordingly
A command c for generating a response pulse (FIG. 2 (c)) as a constant response pulse train is sent to the pulse generator 2, and a response pulse (FIG. 2 (c)) is generated and a response is transmitted. here,
As a response pulse, as shown in FIG. 2C, a three-pulse train is used, and the second pulse is assigned to a distance bit for calculating a distance, and the third pulse is assigned to an azimuth bit for calculating an azimuth.

The transponder 11 receives a three-pulse sequence from the interrogator 1 by a plurality of antennas 17, and performs a three-pulse sequence reception process by a data processor 19 via a receiver 18 using a receiver gate b. Azimuth is calculated by comparing the levels. Further, the data processor 19 calculates the time until receiving the three pulses communicating after north direction reference (NRB) pulse transmission, a predetermined processing time parallel from the time
In addition, the distance to the distance bit of three consecutive pulses is subtracted to obtain the distance. Further, the data processor 19 checks the reception status by three packets.
Judgment is made based on the reception level of the Luz series, and if the 3-pulse series can be received, the azimuth and distance information are normal and the
Receiving condition of Rogeta is judged to be good, also, orientation
In the case of two-pulse consecutive reception excluding the bit, data indicating that only the distance is normal is created. The data processor 19 outputs the information d of the azimuth and distance of the aircraft and the reception state data obtained by the above method to the indicator 20 for display.

Since this device has the same principle as that of the secondary radar, its coverage area is 200 to 300 NM, and it is possible to know the direction and distance of a wide range of aircraft.

[0015]

As described above, according to the bearing / distance measuring device of the present invention, the transponder of TACAN
A response signal indicating the reception status from the interrogator is specified.
The answer is obtained in the form of a pulse train.
Based on the time from the azimuth reference pulse to the reception of the response pulse train,
Zui by bearing and distance of the aircraft, calculate the reception state, since so as to display the determined <br/>, it is possible to know the direction and distance of the aircraft on the ground station. As a result, in the flight inspection of the ground station, it is possible to quickly determine the problem processing such as unlocking. Further, there is an effect that the safety as a navigation assistance system can be further enhanced.

[Brief description of the drawings]

FIG. 1 is a configuration block diagram of an azimuth / distance measuring device according to an embodiment of the present invention.

FIG. 2 is an operation time chart of the azimuth / distance measuring device according to one embodiment of the present invention.

FIG. 3 is a configuration block diagram of a conventional azimuth / distance measuring device.

FIG. 4 is a time chart of various pulses transmitted by a transponder.

FIG. 5 is an explanatory diagram of distance measurement in an interrogator.

FIG. 6 is a radiation pattern diagram of an antenna of a transponder (ground station).

FIG. 7: radiation pattern and reference pulse (NRB, ARB)
FIG.

FIG. 8 is an explanatory diagram of azimuth measurement in an interrogator.

FIG. 9 is an explanatory diagram of azimuth measurement in an interrogator.

[Explanation of symbols]

 Reference Signs List 1 interrogator 6 signal processor 11 transponder 17 antenna (1 to n) 18 receiver 19 data processor 20 indicator

Claims (1)

(57) [Claims] 1. An azimuth / distance measuring device comprising an interrogator mounted on an aircraft and a transponder installed on the ground; a reception state of a north azimuth reference pulse as a specific signal transmitted from the transponder to the interrogator; Means for transmitting a response in the form of a specific response pulse train consisting of a plurality of pulses having a predetermined interval; and enabling the transponder to receive the response transmission of an interrogator and determine the heading of the aircraft. A receiver for receiving and processing the plurality of antennas in an array and the specific response pulse train captured by the plurality of antennas; and an aircraft of the aircraft by the plurality of antennas of the specific pulse train including a reception signal output from the receiver .
The strength of each directional direction formed so that the azimuth can be determined
Data for calculating the direction of the aircraft based on the intensity of the corresponding reception level, determining the quality of the reception state, calculating the distance to the aircraft based on the time from transmission to reception of the north direction reference pulse, and outputting the data. A processing unit; and an indicator for displaying the azimuth and distance output from the data processor and the reception state;