JP2589498B2 - Moving object ground guidance system - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION <Industrial Application Field> The present invention relates to a moving object ground guidance device for safely guiding and controlling a long moving object that is longer than a predetermined length entering or existing on a taxiway in an airport.

<Conventional technology> In order to prevent ground contact and collision accidents between aircraft,
The taxiway was divided into several continuous control sections with a section length of, for example, about 100 m, and aircraft detection devices were installed in each control section so that subsequent aircraft could not enter the control section where aircraft existed. An aircraft ground guidance system has been proposed (Source: Research report on aircraft guidance systems at taxiways and aprons at New Tokyo International Airport)
44 ~ Showa 50, Japan Aviation Promotion Foundation) These are about 90 ~ 10 at the entrance and exit of each control section.
Self-inductance change that occurs when a rectangular loop coil of, for example, 3 to 5 m is placed one by one at a distance of 0 m and the side parallel to the aircraft traveling direction is extremely shorter than the aircraft length, and the aircraft passes through the entrance side loop coil. Is detected by a sensor, and the memory is set to a set state by the sensor signal. As a result, the entry prohibition light is turned on with the presence of the aircraft in the control section, and entry of the subsequent aircraft is prohibited.

When the approaching aircraft passes through the exit loop coil, the memory in the set state is reset by an output signal from the corresponding sensor, the aircraft is absent, the approach permission light is turned on, and the aircraft ahead of the succeeding aircraft is turned on. Permit entry to the control section.

In this way, contact and collision accidents on the ground are prevented by limiting only one aircraft that can exist in one control section.

<Problems to be solved by the invention> By the way, not only aircraft but also various vehicles such as passenger transport buses and maintenance vehicles pass on taxiways, and the self-inductance change occurs in the loop coil due to the passage of these vehicles. An aircraft detection device detection output is generated. In the case of these automobiles, in particular, the vehicle does not always run on the taxiway, may cross the taxiway, and may sufficiently pass only on one of the loop coils on the entrance side or the exit side.

In such a case, in the guidance system based on the set-reset method using the above-described memory, for example, the vehicle is set by passing through the entrance-side loop coil even though the aircraft is not in the control section, and is not reset as it is. And the subsequent aircraft cannot enter even though the aircraft does not exist. Conversely, since the memory of the set state is reset by the vehicle passing over the exit side loop coil, the entry permission lamp is turned on even though the aircraft is in the control section, and the subsequent There is a risk that the aircraft will enter.

Furthermore, this control system is also applicable to a vehicle that is extremely small as compared to an aircraft, and a single vehicle may occupy a control section, and there is a concern that the operating efficiency of the taxiway may be significantly reduced.

The present invention changes the shape and arrangement of a plurality of loop coils provided in each control section of the taxiway so as to eliminate the inconvenience of the above-described device. By detecting a long moving object longer than a predetermined length and a short moving object shorter than a predetermined length so that a long detection object is generated, the presence or absence of a long moving object in a control section is reliably grasped. An object of the present invention is to prevent a subsequent long-moving object from entering a control section where a moving object exists, thereby preventing a rear-end collision of the long-moving object on a taxiway, and enabling safe and efficient guidance of a long-moving object. .

<Means for Solving the Problems> In order to achieve the above object, the moving object ground guidance device according to the present invention is provided in an airport where a long moving object longer than a predetermined length and a short short moving object exist. The guidance path for guiding the long moving object is divided into a plurality of control sections, and for each of these control sections, a loop coil whose coil side along the long moving object traveling direction is shorter than the long moving object and longer than the short moving object. A plurality of loop coils are provided along the traveling direction of the long moving object, and the adjacent coil sides of adjacent loop coils are arranged close to each other so as to be located at substantially the same location, while being provided and corresponding to each of the loop coils. Based on the self-inductance change of the loop coil, a detection output of the presence or absence of a moving object is issued, and the detection output of the presence of a moving object is a low potential output and the detection output of no moving object is a high potential output. A plurality of moving object detection means having a configuration in which the output potential is erroneous to the detection output potential side when there is a failure and the presence of a moving object, and a display indicating that a long moving object is allowed to enter the control section and prohibited from entering. A display unit, and when the output of the moving object detection unit corresponding to the adjacent loop coil in each control section is partially overlapped and continuously generated, a long moving object is determined to be present and the display unit is determined based on the partially overlapped continuous output. And control means for controlling the

In addition, the interval between the plurality of loop coils in the control section may be shorter than the long moving object and longer than the short moving object.

<Operation> As a result, the moving object detection signals of the two moving object detecting means corresponding to the loop coils adjacent to each other are continuously generated while being always partially overlapped only when the object is a long moving object, and this part is overlapped. The display means of the control section is controlled based on the continuous detection output. On the other hand, for a short moving object shorter than a predetermined length, when the loop coil interval is arranged very close so that adjacent coil sides are located substantially at the same position, the two moving object detecting means When the detection output is discontinuous and is an output pattern that occurs and disappears at the same time, and the loop coil interval is set shorter than the long moving object and longer than the short moving object, the detection outputs of the two moving object detecting means are reduced. The output pattern is discontinuous and the detection output does not overlap. Therefore, the output pattern of the moving object detecting means is different from that of the long moving object, and the long moving object and the short moving object can be distinguished. Therefore, the guidance control for the long moving object is not affected by the passage of the short moving object. Further, the control section is not occupied by one short moving object, and a safe and efficient moving object guiding system can be provided.

Embodiment An embodiment of the present invention will be described below with reference to the accompanying drawings.

In FIG. 1, when a long moving object longer than a predetermined length in an airport is an aircraft, and a short moving object shorter than the predetermined length is an automobile, a plurality of moving objects in the aircraft traveling direction on the taxiway 1 (in the direction of the arrow in the drawing) of the aircraft. Loop coil l _i (i = 1,2
..) Are continuously buried in the guide path 1 at extremely close intervals such that adjacent coil sides b are located at substantially the same place. In addition, you may arrange | position so that adjacent coil side b may be shorter than an aircraft and longer than an automobile.

The loop coil l _i has a side a along the aircraft traveling direction of the taxiway 1 shorter than the aircraft length and longer than the vehicle length.
= 30 m, and a side b perpendicular to the side a has a rectangular shape of 30 m. The guide path 1 is divided into a plurality of control sections D having a length of about 100 m, for example, and three loop coils l _i are arranged in each control section D.

Loop coil l _i is the self-inductance is changed by the passage of an aircraft, such changes of the control means the detected presence detection signal of the aircraft at the sensor S _{i (i} = 1,2 ...) corresponding to each loop coil l _i Output to the signal processing device 2.

The signal processing unit 2, the direction-object discrimination circuit 3 for identification of the traveling direction detection and automotive aircraft to be described later, is configured to include a display command circuit 4, a detection signal and traffic controllers from the sensor S _i Each signal light switch for performing NO-OFF of a green signal light G for indicating permission of entry of an aircraft to the control section D or a red signal light R for indicating inhibition of entry based on a command signal from the manually operated device 5 to be operated. It controls the signal light switch circuits 6, 7 as control means.

When the aircraft enters the control section D from the left side in the figure, the sensors S ₁₀ , S ₁₁ , S ₁₂ are sequentially and continuously based on the self-inductance change of the loop coils l ₁₀ , l ₁₁ , l _{12 as} the aircraft travels. when the detection signal from the sensor S ₁₀ to S ₁₂ for outputting a detection signal of the aircraft is output, turns on the signal lamp R as there aircraft control section D control section D of the following aircraft
Prohibit entry to When a non-detection output is generated from a sensor in the control section D after the aircraft in the control section D has entered the front control section and a permission signal is generated from the front control section, the signal light G is turned on and the subsequent Allow aircraft to enter.

Each of the sensors S _i , the signal processing device 2 and the signal light switch circuits 6 and 7 has a fail-safe configuration, and a specific circuit configuration will be described below.

The sensor S _i generates a high level (H level) non-detection output only when the loop coil l _i and the sensor are normal and the aircraft is not present on the loop coil. When present on the loop coil, a low level (L level) detection output is generated.

The circuit configuration is as shown in FIG.
A high-frequency signal generator 12 that is driven by the power supply from the power supply 11 and sends a high-frequency current to the loop coil l _i of the guide path 1;
R _a, R _b, and the loop coil l _i and the bridge circuit 13 constituted by a capacitor C _R in the substantially resonant state with respect to the output frequency of the R _c and the high-frequency signal generator 12, an unbalanced voltage output of the bridge circuit 13 an AC increase width 14 which Zohaba a, a detection circuit 15 for detecting an envelope of the AC output signal of the AC increased width 14, (FIG. 3 when the output e ₂ of the detection circuit 15 is within a certain level range V ₁ <e ₂
<V ₂ ) A window comparator 16 that generates an oscillation output,
Rectifier circuit for rectifying the oscillation output of window comparator 16
17 is provided.

When an aircraft is not present on the loop coil l _i in a state where a high frequency current is supplied to the loop coil l _i by the high frequency signal generator 12, the unbalanced output of the bridge circuit 13 is applied to the AC amplifier as shown in FIG. The output level of output e ₁ amplified by 14 is
a e _11, the output level of the output e ₂ of the next stage of the detector circuit 15 e
It becomes ₂₁ .

In contrast, the loop coils l _i self inductance change imbalance output of the bridge circuit 13 is increased by an AC increased width unit level of the output e ₁ of 14 e ₁₂ of when the aircraft is on the loop coil l _i increases, even the output e ₂ of the detection circuit 15 whose level increases e _22. The magnitude of this change is, for example, in the case of a loop coil 30m × 40m, as shown in FIG.
(A) aircraft (Boeing 747) up to about 0.8%,
In the case of the car (B), the inductance change rate is about 0.3% at the maximum.

Window comparator 16, the output e ₂ of the detection circuit 15 is the output level e ₂₁ during normal aircraft absence and the window has an output level e ₂₂ is outside the window configuration when the aircraft is present and, therefore, when the aircraft is not present oscillates, the rectified output e ₃ of the rectifying circuit 17 becomes a non-detection output of the aircraft absence of high potential (e ₃ = logical value 1), when there is aircraft stops oscillating the to rectified output e ₃ low potential (e ₃
= Logical aircraft value 0). In this manner, by setting the aircraft detection output that inhibits movement of the succeeding aircraft to a low potential output by stopping oscillation, the aircraft detection output can be made to correspond to an output state at the time of an abnormality that does not cause oscillation such as a circuit failure. In this case, fail-safe control for ensuring safety by prohibiting the movement of the succeeding aircraft in the event of an abnormality becomes possible.

Here, an AND operation oscillation circuit which is a basic circuit constituting the window comparator will be described with reference to FIG.

This is a feedback oscillation section including two NPN transistors Q ₁ and Q ₃ , one PNP transistor Q ₂ and eight resistors R _{1 to} R ₈ , a diode D ₁ , an NPN transistor Q ₄ and four resistors R ₉
It is composed of a increasing width portion consisting to R _12. (July 59
The operation is as follows. When no input signal is applied to the input terminals I ₁ and I ₂ , the transistor Q ₁ is off and the transistors Q ₂ and Q ₃ are on.
And no oscillation output is generated from the output terminal f. When the input signal of the predetermined high level is applied than the power supply voltage E _s to the input terminal I _1, I ₂ in this state, the transistors Q ₁ to Q ₃ is oscillated to the output terminal f repeatedly ON-OFF as follows Produces output. That is, Q ₂ OFF → Q ₃ OFF → Q ₁ ON → Q ₂ ON → Q ₃ ON → Q ₁ OF
Increasing width transistor through operation to the oscillation output of the collector of the transistor Q ₃ is a diode D ₁ as F · · ·
It is input to the Q ₄ produce oscillation output from the output terminal f.

The condition of the input signal that generates the oscillation output is substantially as follows when the input voltages of the input terminals I ₁ and I ₂ are VI ₁ and VI ₂ .

Thus, this circuit oscillates only when an input higher than the power supply voltage E _s to the input terminal I _1, I ₂ a predetermined level is applied AN
D gate. Also, if the input terminals I ₁ and I ₂ are common as shown by the dotted lines in the figure, the input voltages VI ₁ and VI ₂ oscillate by the logical product, so the condition of the oscillating input voltage VI (= VI ₁ = VI ₂ ) Becomes as follows.

In this way, the AND logic oscillation circuit shown in FIG. 5 becomes the window comparator used in FIG. 2 when both input terminals I ₁ and I ₂ are common, and the input signal level falls within the range of the equation (3). Oscillation output is generated only at certain times. Incidentally, the input voltage range (window) of the equation (3) can be changed by the value of the resistance constituting the circuit.

Since the above-mentioned circuit does not generate an oscillation output at the time of failure, it has a characteristic that at least an output signal is not erroneously generated when there is no input signal, that is, a fail-safe characteristic.

The rectifier circuit 17 shown in FIG. 2 is a diode shown in FIG.
In the voltage doubler rectifier circuit is clamped to the power supply voltage E _s by D _2, terminal I _3, I ₄ is connected to the power supply line E _s and an output terminal f of FIG. 5, respectively. And window comparator 16
Oscillation time of miso rectified output e ₃ becomes from the high potential power supply voltage E _s of, when the window comparator 16 is failed and of the rectifier circuit 17 when not oscillate, no rectified output of the high-potential than the power supply voltage E _s.

Accordingly, by setting the output e ₂₁ (absence of aircraft) of the detection circuit 15 in the normal state to be within the range of the expression (3) and setting the output e ₂₂ when the aircraft is present to be out of the range, the sensor S _{i is set.} Can be made as shown in FIG.
The window comparator 16 and the rectifier circuit 17 have fail-safe characteristics as described above, and the high-frequency signal generator 12, the AC amplifier 14, and the detection circuit 15 have a known fail-safe configuration that does not generate an output when a failure occurs. Can be realized,
The resistors R _a , R _b , R _c and the capacitor C _R which constitute the bridge circuit 13
When a disconnection or short-circuit failure occurs in the loop coil l _i , the unbalanced output increases significantly and the output of the detection circuit 15
Since e ₂ is a level outside the window of the window comparator 16, the sensor S _i by the configuration of FIG. 2 has a fail-safe characteristics.

 Next, the configuration of the signal processing device will be described.

First, as shown in FIG. 7, the direction / object identification circuit 3 for identifying the traveling direction of an aircraft and a moving object (aircraft and automobile) is shown in FIG. First to third AND gates A ₁ , A ₂ , A ₃ each configured using an AND operation oscillation circuit;
6 and FIG illustrated ones similar to rectifier circuits 23 to 27, the adjacent loop coils l _10, first AND gates A ₁ of the control section between the output of the sensor S _10, S ₁₁ which is connected to the l ₁₁ inputs the input terminal for inputting the output of the sensor S ₁₀ corresponding to the loop coil l ₁₀ located on the inlet side, a first self feeding back the rectified output of said first aND gates a ₁ via the feedback resistor R ₂₁ A holding circuit and a rectified output of the _third AND gate A3 to a second AND gate
Configured to include a second self-holding circuit for feeding back via a feedback resistor R ₂₂ to the input terminal side of the output of A ₂ is inputted.

Here, the output S _i of the sensor S _i to be inputted to the NOT operation circuit 21 and 22 (rectified output e ₃ of the rectifying circuit 17) becomes the H level when the non-detection of the aircraft, a negative signal which becomes L level when detecting (Negative mode for detection) output,
Here, the output signal of the sensor S _i and _{i, i =} 0 when the aircraft is detected, and _{i =} 1 when not detected.

Figure 7 is the output signal of the sensor S _10, S ₁₁ when assumed to move from the loop coil l ₁₀ in the direction of the loop coil l _{11
This is} for detecting the movement of an aircraft by ₁₀ and ₁₁ .

Hereinafter, this operation will be described based on a time chart.

The section where an object is detected by each loop coil l ₁₀ , l ₁₁ is
Threshold value set by the sensor S ₁₀ detects the loop coil l ₁₀ determined by (detection level) valid interval n (n <a)
And the sum (n + m) of the length m of the aircraft floor effective for detection. Since the distance between the loop coil l ₁₀ and l ₁₁ are sufficiently smaller than an aircraft, the detection output _{10, 11} by the loop coil l _10, l ₁₁ is partially generated overlap as shown in FIG. 8 . However, outputs S ₁₀ and S ₁₁ are output signals in the figure.
Negative signals of ₁₀ and ₁₁ .

Detection output ₁₀ of the sensor S _10, S _{11, 11} are NOT operation circuit 2
The signal is input to the _first AND gate A1 via the first and second gates 22. With the movement of the aircraft, the sensor S ₁₀ detects this, the detection output ₁₀ becomes "0" and the first input signal S ₁₀ of the AND gate A ₁ is "1". In this state, when the aircraft detection output ₍₁₁ = 0) is generated from the next sensor S _11, the first other input signal S ₁₁ is "1" and the first AND gate of the AND gates A ₁
A ₁ oscillates, the rectified signal S _a from the rectifying circuit 23 is a second AND
At the same time is applied to one input of gate A _2, rectifier circuit
The first input signal S ₁₀ of the AND gate A ₁ is between self-hold has detected the aircraft via the resistor R ₂₁ by the output of 24.

Second AND gate A ₂ oscillates to generate an output S _b 'for the direction detection output generated as rectified output of the rectifier circuit 25 when the aircraft detection signal of the sensor S _{10 (10} = 0) has been extinguished.
This output S _b ′ is input to the next third AND gate A ₃ and the sensor S
Disappearance of the detection output of _{11 (11} = 1) via a resistor R ₂₂ by the rectifier circuit 26 by the non-detection output of the sensor S ₁₁ from the rectifier circuit 27 of the third AND gate A ₃ is self-holding ₍₁₁ = 1) continue to occur during has occurred, is output as the direction detection output S _b indicating that the aircraft from the direction-object discrimination circuit 3 is moved from the loop coil l ₁₀ to the loop coil l _11.

Then, in the circuit of FIG. 7, when the aircraft is the order of the output signal of the detection by moving in the opposite direction is output in the order of ₁₁ → _10, the first AND gate A ₁ is not self-retained, also the when the output of the first aND gate a ₁ disappears, it still sensor S ₁₀ is the detection output ₍₁₀ = 0) because it generates a second aND gate for direction detection output generated from the a ₂ output S _b ' not occur, it is not generated a third aND gate a ₃ direction detection output from _{S b (S b = 0)} .

Further, the NOT operation circuits 21 and 22 and the first to third AND gates A ₁
To A ₃ and the rectifier circuit 23 to 27 does not cause the output at the time of failure. Further, when a breakage fault occurs in the feedback resistors R ₂₁ and R ₂₂ , the self-holding is not performed, so that a continuous direction detection output does not occur.

Therefore, the direction / object identification circuit 3 has a fail-safe configuration in which a detection output is not erroneously generated due to a failure.

Further, in an automobile having a shorter length than the coil side a of the loop coil l _i , a detection output is generated only near the coil side of the loop coil, and when the distance between adjacent loop coils is longer than that of the automobile, the sensor S ₁₀ , Detection output ₁₀ from S ₁₁ ,
₁₁ does not overlap at the same time, and when adjacent loop coils are in the same place, the output disappears at the same time,
Again, since no direction detection output is generated, the aircraft reacts by overlapping signals from sensors adjacent only to the aircraft, does not respond to the automobile, and can reliably detect the aircraft.

Next, the instruction command circuit 4 for generating an entry permission display command and an entry prohibition signal for the control section will be described with reference to FIG.

If an abnormal situation occurs on the taxiway 1, the instruction shown in FIG. 9 should be taken into consideration, considering that the taxiway 1 should be completely prohibited or the aircraft should be guided (manually operated) by the instruction of the controller. The command circuit 4 has a manual mechanism.

Changeover switch SW ₁ of the manual operation device 5 is normally at the contact point C ₁
While providing travel permission of the taxiway 1 is connected to the side, or the like for providing a driving stop signal to the breach all control section or the particular control section to cancel the running permission to the contact C ₂ side at the time of abnormality intended to function as a cancel switch for canceling all the operations of the switches SW ₂ to SW ₄ which will be described later. The switch SW ₂ is a direction setting switch for the controller to set the direction of travel of the aircraft, and the switch SW ₃ automatically controls the guidance of the aircraft (contact C) when traveling permission is given by the changeover switch SW _{1. 3} side) and either manually (a changeover switch for selecting whether the contact C ₄ side), when the switch SW ₄ is that in manual switch SW _3, appropriately travel by the operation of the air traffic controllers This is a manual traveling permission command switch for providing a permission command signal.

In the display command circuit 4, permission to travel on the taxiway is given.
And the direction instructed by the air traffic controllers, output via a rectifier circuit 31 from the fourth AND gate A ₄ when the direction detection signal S _b from the direction-object discrimination circuit 3 matches occur, at this time If the switch SW ₃ is on the contact C ₃ side, the operation is automatic and the entry permission signal is automatically input to the fifth AND gate A ₅ ,
If the switch SW ₃ is connected to the contact C _{4, the} operation is manual operation, and when the switch SW ₄ is turned on by the controller, an entry permission signal is inputted to the fifth AND gate A ₅ and the _fifth A is inputted.
From ND gate A ₅ to the control section D of FIG. 1 shown in the rear-side control section (individual aircraft currently entering to have control section (corresponding to the front-side control section of the control section D of FIG. 1 shown here) permission signal f ₁ is generated through a rectifying circuit 32 for equivalent), it is applied to one input terminal of the aND gate a ₈ as ingress permission instruction means. That is, the fourth and fifth AND gates A ₄ and A ₅ and the rectifier circuits 31 and 32 constitute an entry permission signal generating means.

On the other hand, loop coils l ₁₀ of the control section in the D, l _11, each sensor S ₁₀ corresponding to l _12, S _11, from any of S _12, the aircraft detection signal ₍₁₀ = ₁₁ = ₁₂ = 0) occurs if not, aND the output through the rectifying circuit 34 of the aND gate a ₇
Gate output f ₂ of A ₆ is applied to the other input terminal of the AND gate A ₈ becomes non inhibition signal of a high potential through the rectifier circuit 33.
Thus, to allow entry into the control section D and entry permission display instruction signal f ₃ of the high potential to turn on the generated signal lamp G from the AND gate A _8.

That is, only when the direction detection output is generated in the forward control section of the control section D in accordance with the direction instructed by the controller and no aircraft is present in the control section D, the entry permission display instruction signal to the control section D is issued for the first time. f ₃ occurs.

If an aircraft exists in the control section D, the sensor
S _10, S _11, the detection output from one of S _{12 (10, 11} or
₁₂ since = 0) is generated, by turning on the output f ₂ enters permission display command signal f ₃ is not generated when the signal light R of no-entry time of the AND gate A ₈ goes low no-entry signal of the AND gate A ₆ The entry into the control section D is prohibited. AND gate A ₆
And the 6 AND gate is constituted of a A _7, constitutes a breach signal generating means and these AND gates A _6, A ₇ by the rectification circuits 33 and 34.

When an abnormal situation occurs in taxiway 1, switch SW ₁
Travel inhibit signal is generated in all the control sections or specific control sections by switching the contact point C ₂ side. Then, the AND gate A ₄ to A ₈ are therefore not generate a fault at the output, a fail-safe arrangement never enters permission signal at this time a high potential is generated. In places where the aircraft travels in both directions,
A circuit having a similar configuration is provided for the other driving direction.

Also, if the aircraft as immediately after switching the direction of the aircraft induced no way yet is the direction detection signal is not generated, non-inhibition signal f _4, for example, FIG generated by non-detection signals from the sensors of the control section generating entry permission display command signals f ₃ to the control section D by which the switch SW ₅ by manual operation as indicated by the middle dotted line provided to generate a re f ₁ and the permission signal f ₁ keep wired OR connection Obviously you can do that.

The respective switch circuits 6 and 7 of FIG. 10 and FIG. 12 the display command entry permission display instruction signal f ₃ and breach signal f ₂ is prohibited for the signal lamp R and authorization signal lamp G is inputted from the circuit 4 Show.

First, the permission signal light switch circuit 6 will be described.

The permission signal light switch circuit 6 uses a solid state relay (hereinafter, referred to as SSR) as a switch element, and the SSR indicates both a disconnection (OFF) or a short circuit (ON) switch state when viewed from the output side when a failure occurs. . Therefore, there is a risk that a signal display mode of either permission or prohibition may be erroneously taken due to a failure.Especially, if a permission signal display occurs, there is a risk that the aircraft will collide. The display of the permission signal must be avoided.

For this reason, the permission signal light switch circuit 6 is provided with a monitoring circuit 50 surrounded by a chain line in FIG. 10 for monitoring whether or not the SSR is operating normally and shutting off the power of the signal light G in the event of an abnormality.

In FIG. 10, the rectifier circuit 41 corresponds to the AND gate A in FIG.
Rectifying the entry permission display command signal f ₃ from ₈ outputs the SSR performing switching of the signal lamp G is. The SSR turns off when a high-potential input signal is input, and turns on when a low-potential input signal is input. In addition, the constant current power supply 42
Is generally used.

On the other hand, the monitoring circuit 50 for monitoring the operation state of SSR comprises a rectifying circuit 51 for generating a superimposed rectified output DC voltages V ₁ to approach permits display command signal f _3, current detector for detecting the presence or absence of the output current of SSR DC voltage at the output of the current sensor 52 as a means
A rectifier circuit 53 for generating a rectified output obtained by superimposing V _1, the AND of the input-output relationship of each value has a window comparator function of logically comparison of both the rectifier circuit 51 and 53 oscillates when the normal The fifth which converts the wired OR output (digital) of the gates 54 and 55 and the AND gates 54 and 55 into analog
A D / A converter 56 comprising an AND gate similar to that shown in the figure;
An electromagnetic relay 59 as a current interrupting means which includes an AC amplifier 57 and a rectifier circuit 58 for rectifying the AC amplifier output, and controls the connection / disconnection of the constant current power supply 42 and the signal lamp G by the rectified output. To control the drive of.

 Next, the operation will be described.

Input signal (entrance permission display command signal f ₃₎ and the output signal in a normal electromagnetic relay 59 is connected to the contact r ₁ side (SS
The relationship of the R output current) is output “0” when the input is “1” and output “1” when the input is “0”. That is, when input “1”, SSR
Is turned off and the signal lamp G is turned on. When the input is "0", the contact of the SSR is turned on and the signal lamp G is short-circuited and turned off.

Now, when the input signal f ₃ from the AND gate A ₈ inputs, outputs obtained by superimposing voltages V ₁ from the rectifier circuit 51 is applied to the input terminal I ₂ of the input terminal I ₁ and the AND gate 55 of the AND gate 54. Furthermore, the rectified output obtained by superimposing voltages V ₁ to the output of the current sensor 52
It is applied to the other input terminals I ₂ and I ₁ of the AND gates 54 and 55.
Here, the power supply voltage V ₂ of both AND gates 54, 55 is changed to rectifier circuits 51, 5
It is set lower than the superposed voltages V ₁ in 3.

The AND gate 54 oscillates when the input signal is “1” and the current sensor output is “0”. The AND gate 55 oscillates when the input signal is “0” and the current sensor output is “1”. When there is an output relationship, both AND gates 54 and 55 do not generate an oscillation output.

Therefore, if the voltages when the input signal and the output signal of the current sensor have the logical value 1 (high potential) are represented by V _f and V _S , respectively, AND
Oscillation condition of the gate 54, the side of the input terminal I ₁ is And the input terminal I ₂ side , And the oscillation condition of the AND gate 55, the side of the input terminal I ₁ is And the input terminal I ₂ side It is.

That is, the logical sum (wired OR) output of the AND gates 54 and 55 becomes the logical value "1" only when the input / output relationship is normal.

Therefore, the D / A converter 56 generates an oscillation output only when the input / output relationship is normal, is amplified by the AC amplifier 57, is rectified by the rectification circuit 58, and is rectified by the rectification output.
There are exemplified by closing the contact r ₁ side. As a result, only when the permission signal light switch circuit 6 is normal, the signal light G is turned on and off according to ON / OFF of the SSR. In addition, at the time of abnormality, the electromagnetic relay 59 is not excited and the signal lamp G does not light.
Here, since the monitoring circuit 50 has a fail-safe configuration that does not generate an output at the time of failure, the permission signal lamp G does not light up erroneously due to the failure of the monitoring circuit 50.

The monitoring circuit 50 detects an abnormality when the input signal is “0” and the sensor output signal is “0”, but thereafter, the input signal changes to “1” and the sensor output signal remains “0”. If there is, the input / output relationship becomes the same as in the normal state, and the abnormality determination up to that point is canceled.

In order to prevent this, for example, as shown in FIG. 11, a self-holding circuit that can preset the D / A converter 56 (in this case,
The D / A converter becomes an AND gate). When a normal signal is generated by the ON operation of the preset switch 60, the signal is held and stored by the feedback resistor R even after the switch 60 is turned off. When the oscillation of the D / A converter 56 is stopped and the self-holding is reset at the time of the abnormality, the normal signal may not be output unless the preset switch 60 is turned on again.

In prohibiting signal lamp switch circuit of Figure 12 (signal lamp switch circuit 7 of FIG. 1), SSR61 the output of the AND gate A ₆ in FIG. 9 as a switching element to be OFF when the ON and L level when the H-level And a prohibition signal light R is connected in parallel with the SSR 61. As the power supply, a constant current power supply 42 similar to the permission signal light G is used.

The operation is, for example, any of the sensors S ₁₀ ,
When S _11, the detection signal from the S ₁₂ (L level) is generated, the output of the AND gate A ₆ is L level. As a result, SSR61 becomes O
It becomes FF and the prohibition signal light R is turned on. Also, the sensors S ₁₀ and S
_11, SSR61 both detection signals a non-inhibition signal f ₂ of the H level from AND gate A ₆ if there is no aircraft control section D does not occurs the generation of S ₁₂ are short-circuited are turned ON inhibition signal lamp R And turn off the light.

By the way, in order to safely guide the aircraft, it is necessary to give special consideration to the guidance control.

One is that since the rear end of the aircraft is at a high position, the sensor output is not detected because the self-inductance change is small even if the loop coil l _i does not completely escape and the rear end remains. This is a consideration for the situation.

For example, if the aircraft control section D in FIG. 1 has passed through the loop coil l _10, l ₁₁ enters, enters permission signal f ₁ for the rear of the control section non-detection output of the sensor S _{11 (11}
= 1) occurs at the time of occurrence. However, yet in practice as described above the rear end of the aircraft may be present in the loop coil l _11. In this case, the loop coil l ₁₁
More on the rear of the loop coil l ₉ clearly as the aircraft is not present, a non-detection output to the sensor S _{9 (9}
= 1) when the has occurred, AND that arithmetically calculates a logical product of the output ₉ of the rectifier output and the sensor S ₉ of the AND gate A ₅ as shown in FIG. 13 as the first entry permission signal f ₁ is generated the gate a ₉ is interposed in front of the aND gate a _8, a configuration to improve safety as entry permission signal output signal f ₁ 'of the aND gate a _9.

Another consideration in aircraft control is guidance control at points where taxiways intersect.

FIGS. 14A to 14C show three different driving patterns at the intersection P. FIG. 14A shows an aircraft in the taxiway 1A traveling from the taxiway 1B to 1C or from the taxiway 1C to 1B. (B) is the taxiway from taxiway 1A when the direction of flight of the aircraft on taxiway 1A that joins the flow of the flying aircraft is fixed.
(C) Two taxiways 1A when a direction permission signal is required for the traveling of the aircraft on taxiway 1A, in which both the approach to taxiway 1B or 1C and the approach to taxiway 1A from taxiway 1B or 1C are performed. And the taxiway 1B.

Then, control sections D ₁ , D ₂ , D ₃ , D
_When an aircraft enters ₄ , the aircraft does not exist at the intersection P, but the wing of the aircraft must not be present. Therefore, the entry permission conditions in this case include the control sections D ₁ , D ₂ , D ₃ , D adjacent to the intersection P including the intersection P.
Must be conditional on the absence of an aircraft in any of ₄ above.

Thereby, in the control section sandwiching the intersection P, the intersections P,
The sensor outputs in each control interval _{D 1 ~D 4, 1, 2} ,
₃ , ₄ (at the time of aircraft detection = ₁ = ₂ = ₃ = ₄ =
0), instead of ₉ in FIG. 13,, ₁ , ₂ ,,
₃ and ₄ an AND output to be input to the AND gate A _9.

Since the signals ₁ , ₂ , _3, and ₄ are erroneously set to 0 when each sensor or loop coil fails, the entry permission signal is not generated at this time, and the configuration is fail-safe.

As described above, if the aircraft is continuously detected by the loop coils l _i continuously arranged on the taxiway 1, it is possible to always determine the presence or absence of the aircraft in the control section without using the memory. Safe and secure aircraft guidance. In addition, a specific output pattern in which the detection output is continuously generated from the sensor only by the aircraft according to the shape and arrangement structure of the loop carp, and the control is performed based on the specific output pattern. This is a fail-safe configuration because the detection signal of the aircraft is set to a low level (including zero output), which is opposite to the normal case, and the control signal is incorrectly set to the prohibition signal side indicating that the aircraft is present when the control system fails. ,
Guidance control of an extremely safe aircraft can be performed.

Next, an embodiment in which signals for entry permission and entry inhibition are obtained redundantly will be described.

Because sensor S _i by the loop coil l _i on the ground induction control system of the present invention is to detect a small signal change, the unreliable are common. Therefore, the sensor S _i reliability of this guidance control system which includes a loop coil l _i
Has a highly dependent on the reliability will be described redundancy control for increasing the reliability of such sensors S _i below.

First, the redundancy control for the generation of the entry permission signal will be described.

FIG. 15, the sensor S ₁₀ to S ₁₂ in the control section D of FIG. 1
This is a direction / object identification signal generating circuit for obtaining a direction / object identification signal for obtaining entry permission based on output signals ₁₀ , ₁₁ , and ₁₂ from the device with redundancy.

In FIG. 15, the direction / object discriminating circuits 71, 72, 73 are constituted by those shown in FIG. 7, and outputs ₁₀ and ₁₁ , ₁₁ and ₁₁ , respectively.
₁₂ , ₁₂ and the sensor output ₁₃ in the next control section are input signals. Therefore, these direction / object identification circuits 71, 72, 73
Generates an output signal of direction / object identification sequentially as the aircraft travels in the control section D. And these direction / object identification signals are at least direction / object identification circuits 71, 72,
The configuration is such that the sensor in the forward direction of the sensor that generates each input signal of 73 generates a non-detection output and is transmitted to the subsequent circuit only after the non-detection output. That is, the output of the sensor S ₉ output signals of the direction-object discrimination circuit 71 corresponding to the loop coil l _{9 9}
Becomes the non-detection output ( ₉ = 1) and AND gate A ₂₁
And a rectifier circuit 74, and a direction / object identification circuit 72.
Is the output ₉ of either of the sensors S ₉ and S ₁₀ or
_{When 10} becomes non-detection output ( ₉ or ₁₀ = 1)
The output signal of the direction / object identification circuit 73 via the AND gate A ₂₂ and the rectification circuit 75 is one of the sensors S ₉ , S ₁₀ , and S _11.
When one of the outputs ₉ , ₁₀ or ₁₁ becomes a non-detection output ( ₉ , ₁₀ or ₁₁ = 1), the AND gate A ₂₃ and the rectifier circuit 76
, And these outputs are output as one direction / object identification signal x by wired OR.

Therefore, when the direction-object discrimination signal x is the sensor S ₉ fails, occurs when passing through the sensor S _12, if the sensor S ₁₀ has failed, occurs when passing through the sensor S _12, the sensor S
_{If 11} fails, it occurs when passing through the sensor S _13,
If the sensor S ₁₂ has failed, already direction-object discrimination circuit 7
Occurring when passing through the sensor S ₁₁ by one.

That is, according to the direction / object identification signal generation circuit of FIG. 15, when any of the sensors S ₉ , S ₁₀ , S ₁₁ , and S ₁₂ fails,
The direction / object identification signal x can be generated by another normal sensor. In addition, fail-safe redundant control is provided in which no direction / object identification signal is generated at least before the normal direction / object identification signal generation point. Therefore, when the direction / object identification signal x is generated, it is possible to generate an entry permission signal for a control section behind the control section D in the direction of travel of the aircraft. It will be controlled safely.

Next, redundancy control for generation of the entry prohibition signal will be described.

In the circuit configuration of FIG. 9, when any of the sensors in the control section in D has failed, no entry signal is generated (non-inhibition signal f ₂ is eliminated). However, in a control section provided with a plurality of sensors, even if one of the sensors in the control section fails, it is not possible to have a certain level of control function in the taxiway 1.
It is necessary for the operation of.

FIG. 16 shows an entry prohibition signal generation circuit for obtaining an entry prohibition signal to the control section D with redundancy when one of the plurality of sensors fails.

In FIG. 16, the AND gate A _31, A _32, A ₃₃ output signals ₁₀ of each sensor S _10, S _11, S _{12, 11, 12} one input to, ₉ and _{10, 10} and _{11, 11} And ₁₂ wired OR outputs are used as the other inputs. Capacitor C ₃₁ ,
C ₃₂ , C ₃₃ and diodes D ₃₁ , D ₃₂ , D ₃₃ are each AND gate A ₃₁ ,
A ₃₂ and A ₃₃ are preset with the rising components of the output signals ₁₀ , ₁₁ and ₁₂ (at the end of aircraft detection by each sensor), and are clamped to the power supply voltage E by diodes D ₃₁ , D ₃₂ and D ₃₃ , respectively. Is done. Each of the AND gates A ₃₁ , A ₃₂ , and A ₃₃ has a self-holding circuit whose output is fed back to one input side via feedback resistors R ₃₁ , R ₃₂ , and R ₃₃ to be self-held.
The AND gate A ₃₄ calculates the logical product of the outputs of the AND gates A ₃₁ and A ₃₂ , and the AND gate A ₃₅ calculates the logical product of the logical product of the AND gate A _{34 and} the output of the AND gate A _33. I do. 81-
88 is a rectifier circuit for rectifying the oscillating output of the AND gate A ₃₁ to A _35.

In addition, the approach permission signal f given from the control section on the front side of the control section D in the aircraft traveling direction is supplied to each of the AND gates A ₃₁ and A ₃₁ via the buffer circuit 89 and the rectifier circuits 90, 91 and 92 formed by the AND gate circuits. is applied to the preset input terminal of the a _32, a _33, the entry permission signal each aND gate a ₃₁ by f, a _32, a ₃₃ is preset.

Next, the operation will be described based on the time chart of FIG.

Adjacent ones to each other of the respective sensors S ₉ to S ₁₃ outputs a detection signal overlap with each other in some sections _{(i =} 0) as shown in Figure with the travel of the aircraft. When the sensor S ₁₀ aircraft enters the control section in the D detects this, since still detection signal from the sensor S ₉ at this time is outputted, it wired OR output of ₉ and ₁₀ and the L level
AND gate A ₃₁ is reset AND eliminates the output U ₁
Both the outputs of the gates A ₃₄ and A ₃₅ disappear, and the entry prohibition signal y is output.

Thereafter, the output ₁₀ of the sensor S ₁₀ by the running of the aircraft
There AND gate A ₃₁ by its rising component changes to a non-detection signal from the detection signal output U ₁ is preset inputs to the AND gate A ₃₄ becomes H level. AND gate A ₃₂ , A ₃₃
The same pattern applies to the outputs U ₂ and U ₃ .

Since the reset states of the AND gates A ₃₁ , A ₃₂ , and A ₃₃ sequentially overlap in some sections thereof, the entry prohibition signal y is
As shown in Figure 17, when the AND gate _A31 is reset,
Until D gate A ₃₃ is preset, in other words, it generated until the aircraft is no longer detected after being detected by the loop coils l ₁₀ by the loop coil l _12.

In inhibit signal generating circuit which operates in this manner, for example if a fault in the loop coil l ₁₀ or the sensor S ₁₀ is generated, the AND gate A from the time of _{9 =} 0 since ₁₀ = 0
The output of the signal ₃₁ disappears and the entry prohibition signal y is generated. Also,
_Although the rising component of ₁₀ does not occur, the AND gate A ₃₁ remains in the reset state. However, when the entry permission signal f from the front control section of the control section D is generated, the AND gate A ₃₁ is preset by this. section is the section up entry permission signal f generated when the detection signal generated when the sensor S _9. The operation of the AND gates A ₃₂ and A ₃₃ is as usual.
Therefore, no entry signal y for the control section D of the failure of the loop coil l ₁₀ or sensor S _10, the sensor in the normal section
It becomes the detection signal S ₉ is applied a section from the time of occurrence.

Also, when the loop coil l ₁₁ or the sensor S ₁₁ has failed, just as the output U ₂ of the AND gate A ₃₂ is in front of the sensor S
Reset when the ₁₀ detection signal is generated, and the entry permission signal f
Until preset by becomes a no-entry signal generation section by AND gate A _32. Again, AND gate A
₃₁ and A ₃₃ operate as usual, so that the section in which the entry prohibition signal y is generated in this case is the same as in the normal state. Loop coil l
Even ₁₂ or if the sensor S ₁₂ has failed, the same way no-entry signal generation section in this case is the same section as usual.

That is, the entry prohibition signal generation circuit of FIG. 16 is configured not to narrow the normal entry prohibition signal generation section even when one of the loop coil l _i or one of the sensors S _i fails, thus deteriorating safety. Fail-safe redundant control that does not occur can be achieved.

If the preset signal of the AND gate A ₃₁ is a wired OR output with the output ₁₁ of the next sensor S ₁₁ as well as the output _{10 of the} sensor S ₁₀ as shown by the dotted line in FIG. 16, the loop coil l ₁₀ or the output U ₁ of the aND gate a ₃₁ at the time of failure of the sensor S ₁₀ can be a rise in the non-detection output generation timing of the sensor S _11, a blocking period by aND gate a ₃₁ to the detection end of the sensor S ₁₁ . An AND gate that uses a failed sensor output as a preset signal remains in a reset state once an entry prohibition signal is generated. Since the permission to enter D can be displayed, guidance control of the aircraft is not interrupted.

<Effects of the Invention> As described above, according to the present invention, a guide path for guiding a long moving object longer than a predetermined length at an airport is divided into a plurality of control sections, and a plurality of loop coils provided in each control section. Is set based on the length relationship between the long-moving object and the short-moving object, thereby distinguishing the short-moving object and the long-moving object according to the output pattern and moving on the taxiway. By reacting to the continuous detection output of only the long-moving object, so as to control the entry of the long-moving object for each control section, in the taxiway, for example, a long-moving object longer than a predetermined length, that is, Only the aircraft can be efficiently and safely guided, and the operating efficiency of the taxiway can be increased, which has a great effect at airports where aircraft take off and land frequently. In case of equipment failure, the output on the low potential side must be
That is, the output form is on the side where the aircraft is present in the taxiway, and the control is the same as when an aircraft is present in the control section, so that subsequent aircraft cannot enter the forward control section and fail-safety can be secured. Excellent safety.

[Brief description of the drawings]

FIG. 1 is a block diagram showing an embodiment of an aircraft ground guidance apparatus according to the present invention, FIG. 2 is a circuit diagram of a sensor of the above embodiment, FIG. 3 is a time chart for explaining the operation of the above sensor, 4 (A) and 4 (B) are diagrams showing a change in the self-inductance of an aircraft and a car in a loop coil, respectively. FIG. 5 is a circuit diagram of a logical product operation oscillator which is a component of a window comparator of the sensor. 6 is a circuit diagram of a rectifier circuit in the sensor, FIG. 7 is a circuit diagram of a direction / object identification circuit of the embodiment, FIG. 8 is a time chart for explaining the operation of the direction / object identification circuit, 9 is a configuration diagram of a display command circuit of the above embodiment, FIG. 10 is a switch circuit diagram for a permission signal lamp of the above embodiment, and FIG. 11 is a circuit diagram showing a main part configuration of another embodiment of the above switch circuit. ,
FIG. 12 is a diagram showing a switch circuit for a prohibition signal light, FIG. 13 is a circuit diagram showing another embodiment of the same instruction command circuit, and FIGS. 14 (A) to (C) are different aircraft traveling patterns of the same embodiment. FIG. 15 is a circuit diagram for generating a direction / object identification signal having a redundant function, FIG. 16 is a circuit diagram of a prohibition signal having a redundant function, and FIG. 17 is the same as FIG. 5 is a time chart for explaining an operation of a prohibition signal generation circuit. 1 ... taxiway, 2 ... signal processing device, 6 ... signal light switch circuit (for entry permission signal light), 7 ... signal light switch circuit (for entry inhibition signal light) G ... entry permission signal light, R ... entry prohibition Signal light l _i …… Loop coil, S _i …… Sensor, D …… Control section

 ──────────────────────────────────────────────────の Continuing from the front page Judge Chief Judge Toshiro Tamura Judge Kenji Nishino Judge Masahiro Kawamoto (56) References JP-A-53-131698

Claims (23)

(57) [Claims] 1. A taxiway for guiding a long moving object in an airport where a long moving object longer than a predetermined length and a short moving object are present are divided into a plurality of control sections, and for each of these control sections, The coil side along the long moving object traveling direction is a loop coil shorter than the long moving object and longer than the short moving object,
A plurality of loop coils are provided along the traveling direction of the long moving object, and adjacent coil sides of adjacent loop coils are arranged close to each other so as to be located at substantially the same location, while being provided and corresponding to each of the loop coils. A detection output for the presence or absence of a moving object is issued based on a change in the self-inductance of the loop coil, and a detection output for the presence of a moving object is a low-potential output, a detection output for no moving object is a high-potential output, and an output potential is output in the event of a failure. A plurality of moving object detecting means erroneously arranged on the detection output potential side of the presence of a moving object, display means for displaying entry permission and prohibition of entry into the control section for a long moving object, When the output of the moving object detecting means corresponding to the matching loop coil is partially overlapped and continuously generated, it is determined that there is a long moving object, and based on the partially overlapped continuous output, Moving object ground induction apparatus characterized by being configured to include a control means for controlling the shown means. 2. A moving object detecting means, comprising: a high-frequency signal generator; a bridge circuit including a resonance circuit of a loop coil and a capacitor which is substantially in resonance with three resistors and an output frequency of the high-frequency signal generator. An AC amplifier for amplifying the output of the bridge circuit, a detection circuit for detecting the envelope of the amplified output of the AC amplifier, and a moving object on an induction path using the output of the detection circuit as an input signal. When the detection circuit output level is not present in the window and the moving object is present and the self-inductance of the loop coil is changed, the detection circuit output level has a window characteristic of being outside the window, and the input signal of the window level is not present. 2. The moving object ground according to claim 1, further comprising a window comparator that generates an output when input, and a voltage doubler rectifier circuit that rectifies the output of the window comparator. Electrical apparatus. 3. The first and second of the AND operation oscillating means for generating an oscillation output from an output terminal when an input signal of a predetermined level higher than a power supply voltage is simultaneously applied to first and second input terminals. 3. The moving object ground guidance apparatus according to claim 2, wherein the second input terminals are connected to each other. 4. The AND operation oscillating means includes a second transistor having a collector connected to the first input terminal of the AND operation oscillating means via a first collector resistor and an emitter connected to a power supply input terminal. And a voltage dividing resistor connected between the collector of the first transistor and the ground via a second and a third collector resistor having an emitter connected to the power input terminal and a collector connected in series. A second transistor having its base input with the collector voltage of the first transistor obtained as described above, and a collector voltage of the second transistor divided by the second and third collector resistors being input to its base, and having the collectors of the fourth and fourth collectors. A third transistor connected to the second input terminal of the AND operation oscillation means via a fifth collector resistor and having an emitter connected to the ground. An input signal voltage, which is divided by the fourth and fifth collector resistors and applied to the second input terminal, is input to the base of the first transistor via a resistor, and the collector of the third transistor is connected. 4. The moving object ground guidance device according to claim 3, wherein the moving object ground guidance device is configured to be connected to the output terminal of the AND operation oscillating means. 5. The moving means detects a traveling direction of a long moving object and distinguishes a long moving object from a short moving object based on an output pattern from a moving object detecting means corresponding to a loop coil in a control section into which the moving object has entered. Direction and object identification circuit
Based on the output of the direction / object discriminating circuit and the output of the moving object detecting means corresponding to the loop coil in the control section behind the control section where the long moving object is entering, the entry of the long moving object into the rear control section is permitted. The moving object ground guidance device according to claim 1, further comprising an instruction command circuit that generates a command signal or an entry prohibition signal. 6. The direction / object discriminating circuit is configured to generate a high-potential direction detection output only when a long moving object moves from an entrance side to an exit side of a control section. The moving object ground guidance device as described in the above. 7. A direction / object discriminating circuit, comprising: a first AND gate to which an output of each of the moving object detecting means connected to each of the loop coils adjacent to each other is inputted via each inverter; The rectified output of the AND gate is connected to the loop coil located on the control section entrance side of the loop coil, and the output of the moving object detection means is input to the input terminal side of the first AND gate, which is fed back via a resistor. A first self-holding means for self-holding the output of the first AND gate; and an output of the first AND gate and an output of the moving object detecting means connected to the control section entrance side loop coil. And a third AND gate to which a rectified output of the second AND gate and an output of the moving object detecting means connected to the control section exit side loop coil are input. Third AND output of the rectified output of the third AND gate a second AND gate inputs
7. The moving object ground guidance apparatus according to claim 6, further comprising: a second self-holding unit that feeds back via a resistor to an input terminal side of the gate and self-holds a third AND gate output. 8. A first AND gate, a second AND gate and a third AND gate are connected to an output terminal when an input signal of a predetermined level higher than a power supply voltage is applied to the first and second input terminals. 8. The moving object ground guidance device according to claim 7, comprising a logical product operation oscillating means for generating an oscillation output. 9. An instruction command circuit, wherein a direction setting signal input from a manual operation device operated by a controller matches an output signal from the direction / object identification circuit, and a travel permission signal from the manual operation device. At least one of an access permission signal generating means for generating an access permission signal of a high potential when the signal is input, and at least each moving object detecting means connected to a loop coil in a control section behind a control section in which a long moving object is entering. When a long-moving object detection signal is generated from any one of them, a low-potential entry prohibition signal for prohibiting a long-moving object from entering the rear control section is generated, and a low-potential entry prohibition display command is issued to the display means. An entry prohibition signal generating unit that emits a signal, and the input permission signal generation unit generates the entry permission signal, and only when the entry prohibition signal generation unit does not generate the entry prohibition signal. High potential moving object ground guidance system paragraph 5, wherein the range of configured claims and a penetration permission command means for issuing a display command signal for entering permission on the display means. 10. A fourth AND gate for inputting an output of said direction / object discriminating circuit and said direction setting signal of said manual operation device, respectively, and said fourth AND gate.
The moving object ground guidance device according to claim 9, further comprising a fifth AND gate configured to input a rectified output of a gate and the travel permission signal from the manual operation device. 11. The fourth and fifth AND gates each generate an oscillation output from an output terminal when an input signal of a predetermined level higher than a power supply voltage is applied to the first and second input terminals. 11. The moving object ground guidance device according to claim 10, comprising a logical product operation oscillating means. 12. The moving object ground guidance according to claim 9, wherein the entry prohibition signal generating means includes a sixth AND gate which receives each output of each of the moving object detecting means as an input. apparatus. 13. A AND operation generating and oscillating means for generating an oscillation output from an output terminal when an input signal of a predetermined level higher than a power supply voltage is applied to first and second input terminals. 13. The moving object ground guidance device according to claim 12, which is configured. 14. The system according to claim 9, wherein said entry permission command means includes a seventh AND gate to which each output of said entry permission signal generation means and said entry inhibition signal generation means is input. Moving object ground guidance device. 15. The AND operation generating and oscillating means, wherein a seventh AND gate generates an oscillation output from an output terminal when an input signal having a predetermined level higher than a power supply voltage is applied to first and second input terminals. 15. The moving object ground guidance device according to claim 14, comprising: 16. A manual operation device comprising: a changeover switch for switching between automatic control and manual control of the display means; and a direction setting switch for generating the direction setting signal for setting a long moving object traveling direction of the guideway. A manual travel permission command switch for causing the controller to arbitrarily generate the travel permission signal to the control section when the changeover switch is on the manual control side; and the changeover switch, the direction setting switch, and the manual travel permission command switch. 10. The moving object ground guidance device according to claim 9, further comprising: a driving prohibition command switch for canceling said command signal to generate a driving prohibition command signal. 17. The display command circuit, wherein the direction setting signal input from the manual operation device operated by the controller matches the output signal from the direction / object identification circuit, and the travel permission signal is output from the manual operation device. When a signal is input and a non-detection signal is generated from the moving object detection means connected to the loop coil arranged in a predetermined section in the control section behind the control section in which the long moving object has entered. A length of at least one of an entry permission signal generating means for generating a high potential entry permission signal and at least one of the moving object detection means connected to a loop coil in a control section behind a control section in which a long moving object is entering. When a moving object detection signal is generated, a low potential long moving object entry prohibition signal to the rear control section is generated and a display command signal for prohibiting low potential entry to the display means is issued. An entry prohibition signal generation unit, the entry permission signal generation unit generates the entry permission signal, and only when the entry prohibition signal generation unit does not generate the entry prohibition signal, the display unit outputs a high potential entry permission signal. 6. The moving object ground guidance device according to claim 5, comprising an approach permission command means for issuing a command signal. 18. A display device comprising: an entry permission signal light for supplying power to a long moving object to a forward control section using a constant current source as a power source; and a command from the entry permission command means. Access permission light switch control means for ON-OFF control of the permission signal light, an entry prohibition signal light powered by a constant current source for indicating entry prohibition of a long moving object into the forward control section, and the entry prohibition signal generation means 10. The moving object ground guidance device according to claim 9, comprising: an entry-prohibition light switch control means for controlling the entry-prohibition signal light to be turned on / off based on a command from the controller. 19. An entry permission light switch control means includes: the constant current power supply; the entry permission signal light connected to the constant current power supply; and the entry permission signal light connected in parallel with the entry permission signal light in response to an input signal. Switch element for controlling current supply to the switch, current detection means for detecting an entry permission signal lamp supply current controlled by the switch element, and the entry permission light switch based on an input signal and detection means of the current detection means. A claim comprising: monitoring means for monitoring whether the control means is normal or abnormal; and current interrupting means for interrupting connection between the constant current power supply and the entry permission signal lamp when the monitoring means detects an abnormality. 19. The moving object ground guidance device according to claim 18. 20. The entry-prohibition light switch control means includes a low-potential low-potential signal including the constant-current power supply, the entry-prohibition signal light connected to the constant-current power supply, and an output at the time of failure that is connected in parallel with the entry-prohibition signal light. Turns off when an input signal is input, and when a high-potential input signal that does not include the fault output is input
19. The moving object ground guidance device according to claim 18, comprising a switch element that is turned on. 21. A control device, comprising: an output signal of moving object detecting means adjacent to each other in the control section which sequentially generates a moving object detection output in accordance with the movement of the long moving object; A plurality of direction / object identification circuits for detecting the traveling direction of the object, and the output of each direction / object identification circuit as one input signal, and the direction / direction from the final moving object detection means in the control section behind the control section. A plurality of ANDs, each of which uses the wired OR output of each output of the moving object detecting means up to one before the moving object detecting means located on the opposite side to the moving object detecting means for inputting a signal to the object identifying circuit as the other input signal A gate, and a wired OR circuit for calculating the logical sum of the outputs of these AND gates, and outputs the output of the wired OR circuit to the entry permission signal for a control section behind the control section. Moving object ground guidance system Claims preceding claim configured to include a direction-object discrimination signal generating redundant control means for the direction-object discrimination signal for forming. 22. A display command circuit, wherein a logical sum output of adjacent moving object detection means for sequentially and continuously generating a moving object detection output in accordance with the movement of a long moving object is used as a reset signal, and said adjacent moving object is output. The output signal rising component of the moving object detecting means on the long moving object traveling direction side of the object detecting means or the subsequent to the long moving object entering control section generated from the control section ahead of the control section where the long moving object is entering. A plurality of AND gates having the entry permission signal for a long moving object as a preset signal, and a plurality of self-holding the rectified outputs of the respective AND gates to the preset signal input terminals of the respective AND gates to respectively hold the AND gate outputs. A self-holding circuit; and another AND gate that inputs each output of the plurality of AND gates, wherein one of the plurality of AND gates is provided.
6. The moving object ground guidance apparatus according to claim 5, further comprising an entry inhibition signal generation redundant control unit that outputs a low-level entry inhibition signal including a failure output when one of them does not generate an output. 23. A guideway for guiding a long moving object in an airport where a long moving object longer than a predetermined length and a short short moving object exist, are divided into a plurality of control sections, and for each of these control sections, A plurality of loop coils whose coil sides along the long moving object traveling direction are shorter than the long moving object and longer than the short moving object are provided along the traveling direction of the long moving object, and an interval between the plurality of loop coils is set to the long moving object. While being arranged to be shorter than the object and longer than the short moving object, a detection output of the presence or absence of the moving object is issued based on a change in self-inductance of the corresponding loop coil provided for each loop coil, A plurality of movements in which the detection output is a low-potential output, the detection output without a moving object is a high-potential output, and in the event of a failure, the output potential is erroneous to the detection output potential side with a moving object Body detection means, display means for displaying entry permission and prohibition of entry into the control section for a long moving object, and part of the output of the moving object detection means corresponding to the adjacent loop coil in each control section. A moving object ground guidance device, comprising: a long moving object when it occurs repeatedly and continuously; and control means for controlling the display means based on the partially overlapping continuous output.