JP2544577Y2 - Aircraft guidance equipment - Google Patents

Description

[Detailed description of the invention]

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a guidance device for guiding an aircraft to stop at an apron in an airfield at a predetermined position.

[0002]

2. Description of the Related Art Generally, an aircraft is parked in an apron at an airfield to get on and off passengers, refuel, check equipment, and the like. At this time, the aircraft is guided to a predetermined stop position. It must be stopped accurately. When a crew member (or a worker) in the passenger compartment stops the aircraft visually, it detects that a loop coil embedded in the ground corresponding to the stop position of the apron and that there has been a magnetic field change in the loop coil And a display that is installed in a place visible from the passenger compartment of the aircraft and performs display such as lighting based on the detection signal of the detector, and when an aircraft wheel comes over the loop coil, There is known an apparatus in which a change in the accompanying magnetic field is detected by a detector and an indicator is operated based on the detection signal.

[0003]

However, in this conventional device, since a change in the magnetic field due to the presence or absence of wheels is detected, a complicated circuit is required for the detector for detecting the change in the magnetic field. However, even if the wheel is slightly away from the position directly above the loop coil, a change in the magnetic field occurs and the detection accuracy has a wide range, so that accurate detection is difficult, and there are also dissatisfactions in terms of reliability.

The inventor of the present invention has proposed a detector for detecting the arrival of a wheel of an aircraft guided on an apron in an airfield. A seat plate inserted so as to be able to protrude and retract, a spring for urging the seat plate in a direction protruding from the groove, a shaft connected to a lower portion of the seat plate, and arranged in the groove, into the groove of the seat plate. A proximity switch that detects the approach of the shaft due to immersion and outputs a signal, and when the seat plate is immersed in the groove due to the pressure of the wheel and the shaft approaches the proximity switch, the signal of this proximity switch To detect the arrival at a predetermined position. As described above, the approaching operation of the seat plate and the moving member due to the pressure of the wheel is detected by the proximity switch, and the arrival of the wheel is determined based on the ON / OFF signal of this switch. Detection can be performed with high precision and accuracy,
Reliability can also be improved.

However, in this case, since a groove is formed in the apron and the detector is embedded therein, it is inevitable that the proximity switch of the detector is exposed to intrusion of rainwater, dust, etc. Must solve these problems.

The present invention has been made in view of the above points, and an object of the present invention is to improve the practicality of a detector by taking measures against the intrusion of water, dust and the like in the proximity switch of the detector. Accordingly, it is an object of the present invention to accurately detect the arrival of the wheels of the aircraft guided by the apron with a simple configuration, thereby improving the stopping accuracy of the aircraft and improving the reliability.

[0007]

In order to achieve this object, according to the present invention, a switch housing member having a substantially closed box shape is buried in a groove in the ground, and a proximity switch is housed in the switch housing member. In the switch accommodating member, a waterproof member and a dustproof structure are provided at a portion where the moving member integrated with the seat plate passes.

Specifically, in the present invention, a detector for detecting the arrival of the wheels of the aircraft at a predetermined position in the apron is provided as a guidance device for guiding the aircraft with the apron in the airport.

The detector is inserted into a groove which is open to the ground of the apron and in which the wheel of the aircraft is not immersible, so as to be able to protrude and retract from the apron ground and protrude above the apron ground. A seat plate, a biasing means for biasing the seat plate in a direction protruding from the inside of the groove onto the ground of the apron, and a substantially closed box shape fixed to the bottom of the groove and having an insertion hole formed through the upper surface. A switch housing member, an upper end connected to a lower portion of the seat plate, a lower end slidably penetrating the insertion hole and extending into the switch housing member, and a moving member extending to the bottom of the switch housing member. A proximity switch for detecting that the moving member has approached due to the seat plate being immersed in the groove and outputting a signal; and a switch between the lower portion of the seat plate and the upper surface of the switch housing member around the insertion hole. , Protruding from the switch housing member The portion in which and a stretchable tubular shielding member covering airtightly.

In the invention of claim 2, in addition to the above structure, an outer frame is buried in the groove, the switch accommodating member is fixed inside the groove, and the peripheral edge of the seat plate is brought into close contact with the opening of the outer frame, so that there is a gap between the two. Gaps were eliminated.

That is, in the present invention, an outer frame which has an opening which is open above the size of the aircraft so that the wheel of the aircraft cannot be immersed and which is fitted with the seat plate so as to be able to protrude and retract is fitted into the groove. A switch housing member is fixed to the bottom of the outer frame,
A locking portion projecting toward the center of the opening is formed at the periphery of the opening of the outer frame, while an inclined surface is formed at the periphery of the seat plate, which is inclined upward and toward the center of the seat plate. And
The inclined surface is configured to be in sealing contact with the locking portion when the seat plate protrudes.

[0012]

With the above arrangement, according to the first aspect of the present invention, when the wheel of the aircraft to be stopped rides on the seat plate of the detector, the seat plate acts against the urging of the urging means. Immerse into the ditch from above the ground. With this immersion operation, the moving member connected to the seat plate moves downward to approach the proximity switch in the switch housing member, and the proximity switch outputs a signal due to the approach of the moving member. The arrival of the wheels can be detected with a simple circuit with high accuracy by the signal of the proximity switch, and the reliability can be improved.

At this time, the proximity switch is housed inside a substantially closed box-shaped switch housing member, and a portion of the moving member protruding from the switch housing member is a lower portion of the seat plate and an upper surface of the switch housing member on the periphery of the insertion hole. Is covered with a cylindrical shielding member provided between the switch housing member and the insertion hole on the upper surface of the switch accommodating member, so that the shielding member hermetically covers the outside from the outside. For this reason, even if rainwater, dust, or the like intrudes into the outer frame, it can be reliably prevented from further intruding into the substantially closed box-shaped switch housing member from the gap between the insertion hole and the moving member. Thus, the proximity switch in the switch housing member does not come into contact with water or dust, and the practicality of the detector can be improved.

In the detector, a seat plate which comes into contact with the wheel of the aircraft protrudes from the ground of the apron, and the proximity switch is housed in the switch housing member, connected to the seat plate and inserted into the switch housing member. Since the portion of the movable member exposed from the switch housing member is covered with the shielding member, the seat plate is in contact with the wheel as compared with a structure in which the entire detector is covered with an elastic material and the elastic material is brought into contact with the wheel. In addition, a wear-resistant material can be used to secure the wear resistance, and only a necessary portion around the proximity switch can be sealed from the outside to form a simple seal structure, thereby improving reliability.

According to the second aspect of the present invention, when the seat plate is protruded by the urging means, the inclined surface of the peripheral edge of the seat plate comes into sealing contact with the locking portion of the peripheral edge of the opening of the outer frame. I do.
That is, this contact is a line contact because the contact surface on the seat plate side is an inclined surface, and the opening of the outer frame is securely closed by the seat plate. Therefore, the intrusion of dust and the like into the outer frame can be stably and effectively suppressed, and the intrusion of dust and the like into the switch housing member can be more reliably prevented.

[0016]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiments of the present invention will be described below with reference to the drawings.

FIG. 4 shows the overall configuration of the aircraft guidance system according to the embodiment of the present invention, where Ap is an apron of an airfield, and a straight guide line Lg for guiding the aircraft Ac is provided on the ground of the apron Ap. A stop line Ls and a caution line Lc (caution line) orthogonal to Lg are drawn. The above-mentioned stop line Ls is a short line for positioning the stop position of, for example, the front wheel W of the aircraft Ac guided along the guide line Lg.
The caution line Lc is for notifying the occupant (or worker) of the aircraft Ac that the vehicle is approaching the stop position before reaching the stop line Ls.
It is drawn to the same length as s.

In the guide line Lg, the stop line L
s is a stop position before and after the aircraft Ac, and a position on the guide line Lg that intersects the caution line Lc is a caution position. The stop position and the caution position are the arrival of the wheels W at the respective positions. Are detected. The detectors 1 and 2 have the same configuration. Here, the detector 1 at the stop position will be described. That is, as shown in FIGS. 1 and 3, the ground at the stop position is, for example, one long along the stop line Ls.
A square groove 3 having a bottom of about m is formed, and the detector 1 is fitted in the square groove 3. The detector 1 has a rectangular box-shaped outer frame 4 opened upward, and the width (length along the guide line Lg) of the opening 4a of the outer frame 4 is set to the wheel W of the aircraft Ac.
Are of a size that cannot be immersed (see FIG. 2). Outer frame 4
At the periphery of the opening 4a, a locking portion 5 projecting by a predetermined size toward the center of the opening 4a is formed, and this locking portion 5 also serves as a stopper of a seat plate 6 described later.

A seat plate 6 is inserted into the upper portion of the outer frame 4 so as to be able to protrude and retract from the ground of the apron Ap through the opening 4a and protrude from the ground of the apron Ap. The seat plate 6 has a substantially trapezoidal cross section, and an inclined surface 7 that is inclined upward and toward the center of the seat plate 6 is formed at the peripheral edge thereof. Is projected from the opening 4a of the outer frame 4, the inclined surface 7 is
, In a line contact state (sealed state), and further projection of the seat plate 6 is regulated.

On the other hand, a rectangular cylindrical inner frame 8 as a switch accommodating member extending along the outer frame 4 is fixed to the inner bottom portion of the outer frame 4, and both ends of the inner frame 8 are substantially airtightly closed. It has a closed box shape. Multiple (for example, three) on the upper wall of the inner frame 8
Are formed at regular intervals in the longitudinal direction (see FIG. 3). The upper ends of the shafts 10, 10,... Are integrally fixed to the lower portion of the seat plate 6. Each of the shafts 10 is slidably inserted into the shaft insertion hole 9 of the inner frame 8 with a rubber bush 11 interposed therebetween, and has a lower end extending into the inner frame 8. Between the lower surface of the seat plate 6 and the upper surface of the inner frame 8, a coil spring 12 located around a portion of the shaft 10 above the inner frame 8 is contracted. An urging means for urging the apron 6 from the opening 4a of the outer frame 4 in the direction in which the apron Ap projects above the ground (upward) is constituted.

Further, the proximity switch 2 is located on the upper surface of the bottom wall of the inner frame 8 just below the shaft insertion holes 9, 9,.
Are attached. As shown in FIG. 2, in each of the proximity switches 21, when the wheel W of the aircraft Ac rides on the seat plate 6, the seat plate 6 sinks into the outer frame 4 and the lower end of the shaft 10 approaches. Sometimes, it detects that and outputs a signal.

In each of the shafts 10, the inner frame 8
A portion of the bellows member 13 is hermetically sealed on the lower surface of the seat plate 6, and the lower end thereof is airtight on the upper surface of the inner frame 8 around the insertion hole 9. The inner frame 8 by the bellows member 13.
Of the shaft 9 or the projecting portion of the shaft 10 is hermetically shielded from the outside.

As shown in FIG. 4 again, each proximity switch 21 of the detectors 1 and 2 at the stop position and the caution position is used.
Are connected to the control board 22. In front of the guide line Lg, a display 23 for displaying, for example, by lighting a colored lamp toward the aircraft Ac on the guide line Lg is provided. The display 23 is connected to the control board 22. When the wheel W of the aircraft Ac guided along the guide line Lg arrives at the caution position or the stop position, the signal of the proximity switch 21 of the detectors 2 and 1 for detecting the fact is output to the control board 22. And control board 22
Is displayed on the display unit 23 by the control in step (1).

Next, the operation of the above embodiment will be described. In a normal state, as shown in FIG.
Is protruded above the ground of the apron Ap by the urging force of the spring 12. In this state,
Each proximity switch 21 does not output a detection signal, and the display 23
Is not activated. Also, the inclined surface 7 at the periphery of the seat plate 6 is in line contact with the locking portion 5 at the periphery of the opening 4a of the outer frame 4,
For this reason, the opening 4 a of the outer frame 4 is sealed by the seat plate 6 and is reliably closed, so that the intrusion of dust and the like into the outer frame 4 can be stably and effectively suppressed.

In this state, when the aircraft Ac is guided forward along the guide line Lg of the apron Ap, and its front wheel W rides on the seat plate 6 of the detector 2 at the caution position, as shown in FIG. The seat plate 6 is pushed down against the urging force of the spring 12 and sunk into the outer frame 4. With this immersion operation of the seat plate 6, each shaft 10 connected to the seat plate 6 moves downward, and the lower end thereof approaches the proximity switch 21,
When the shaft 10 approaches, the proximity switch 21 outputs a detection signal. The control board 22 outputs a display signal to the display 23 in response to the detection signal from the detection switch 21, and the display 23 displays, for example, a yellow lamp to indicate "caution". By looking at the display of the "caution", the crew (or the worker) can know that the aircraft Ac has approached the stop position,
Operations such as deceleration can be performed.

At this time, since the seat plate 6 is long in the direction orthogonal to the guide line Lg and a plurality of proximity switches 21, 21,... Are arranged at intervals in the length direction, the wheel W is connected to the guide line Lg. Even if the distance is slightly different from Lg, one of the proximity switches 21 performs the detection operation, and the wheel W
Can be detected more reliably than the detection of the arrival of.

Thereafter, when the aircraft Ac further moves forward and the front wheel W rides on the seat plate 6 of the detector 1 at the stop position, the seat plate 6 is pushed down against the urging force of the spring 12, and Immerse yourself in frame 4. With the immersion operation of the seat plate 6, the same movement as described above is performed, and the proximity switch 21 outputs a detection signal. When the control board 22 receives the detection signal from the detection switch 21 and operates, the display 2
In 3, for example, a red lamp is lit to indicate "stop", and by seeing the "stop" display, the occupant (or worker) can stop the aircraft Ac immediately, and this The aircraft Ac is stopped exactly at the stop position.

Therefore, in this embodiment, since the approaching operation of the seat plate 6 and the shaft 10 due to the pressure of the wheel W is detected by the proximity switch 21, a complicated circuit is not required for detecting the arrival of the wheel W of the aircraft Ac. Becomes In addition, the detection can be accurately performed with high accuracy, and the stopping accuracy of the aircraft Ac at the stopping position can be increased, and the reliability can be improved.

Each of the proximity switches 21 is housed in a closed box-shaped inner frame 8, and a shaft 10 is inserted into each of the through holes 9 as openings of the inner frame 8. The upper part projecting from the inner frame 8 is covered with a cylindrical bellows member 13, and the upper and lower ends of the bellows member 13 are airtightly provided on the lower part of the seat plate 6 and the upper surface of the inner frame 8 around the insertion hole 9 respectively. Since they are joined, the respective insertion holes 9 on the upper surface of the inner frame 8 are airtightly covered with the bellows member 13 from the outside. As a result, in combination with the bush 11 being interposed between the insertion hole 9 and the shaft 10, even if rainwater, dust, or the like enters the outer frame 4, it does not Intrusion into the inner frame 8 from the gap with the shaft 10 can be reliably prevented. Thus, the proximity switch 21 in the inner frame 8 does not come into contact with water or dust due to a synergistic effect with the shielding effect due to the line contact between the seat plate 6 and the locking portion 5 of the outer frame 4, and therefore, it is practically used. Detectors 1 and 2 with high reliability can be obtained.

Further, among the components of the detectors 1 and 2,
The seat plate 6 which comes into contact with the wheel W of the aircraft Ac protrudes above the ground of the apron Ap, the proximity switch 21 is accommodated in the inner frame 8, and the shaft 10 exposed from the inner frame 8 is covered with the bellows member 13. Therefore, the seat plate 6 in direct contact with the wheel W can be made of a wear-resistant material as compared with a structure in which the entire detectors 1 and 2 are covered with an elastic material and the elastic material is brought into contact with the wheel W. In addition, the wear resistance can be ensured, and only a necessary portion around the proximity switch 21 can be sealed from the outside to simplify the sealing structure, thereby improving reliability.

[0031]

As described above, according to the first aspect of the present invention, when the aircraft is guided to stop at a predetermined position of the apron at the airport, the detector for detecting the arrival of the wheels of the aircraft is as follows. A seat plate is disposed in a groove in the ground of the apron so as to protrude above the ground of the apron, and a substantially closed box-shaped switch receiving member is fixed to the bottom of the groove, and the seat plate is placed in the switch receiving member. A proximity switch that outputs a signal when the moving member moves integrally with the housing is housed, and the insertion part of the moving member in the switch housing member is made waterproof and dustproof by a shielding member, so that the seat plate that comes into contact with the wheel is resistant. The switch has a simple seal structure that can be made of abradable material and seals only necessary parts around the proximity switch from the outside while securing its wear resistance. Rain water or dust from entering into the switch housing member can be reliably prevented. For this reason, the use of the proximity switch eliminates the need for a complicated circuit for detecting the arrival of the wheels of the aircraft guided by the travel, and allows the detection to be performed accurately, thereby increasing the stopping accuracy of the aircraft. Thus, a detector that can improve reliability can be put to practical use.

According to the second aspect of the present invention, an outer frame into which the seat plate is inserted is buried in the groove, and a locking portion projecting toward the center of the opening is provided on the periphery of the opening of the outer frame. On the other hand, on the peripheral edge of the seat plate, an inclined surface that is inclined upward to the center portion of the seat plate is formed, and this inclined surface is brought into sealing contact with the locking portion in a protruding state of the seat plate. When the seat plate is in the protruding state, the inclined surface of the peripheral edge of the seat plate is brought into line contact with the locking portion of the peripheral edge of the opening of the outer frame, and the opening of the outer frame is sealed with the seat plate and securely closed. Therefore, it is possible to further effectively prevent dust and the like from entering the switch housing member,
The practical application of the detector can be further enhanced.

[Brief description of the drawings]

FIG. 1 is an enlarged sectional view showing a normal state of a detector.

FIG. 2 is a view corresponding to FIG. 1 showing a detection state of arrival of a wheel by a detector.

FIG. 3 is a plan view of the detector.

FIG. 4 is a plan view showing an entire configuration of the guidance device in the embodiment of the present invention.

[Explanation of symbols]

 Reference numerals 1 and 2 Detector 3 Square groove 4 Outer frame 5 Locking portion 6 Seat plate 7 Slope 8 Inner frame (switch accommodating member) 9 Shaft insertion hole 10 Shaft (moving member) 12 Spring (biasing means) 13 ... Bellows member (shielding member) 21 ... Proximity switch 22 ... Control board 23 ... Display Ap ... Apron Ac ... Aircraft W ... Wheel

Claims (2)

(57) [Scope of request for utility model registration] 1. A guidance device for guiding an aircraft by an apron in an airfield, wherein a detector is provided at a predetermined position on the apron to detect the arrival of wheels of the aircraft, and the detector is provided on the ground of the apron. Open the apron ground into a groove that is open and airplane wheels are
A seat plate inserted so as to be able to submerge and protrude above the ground of the apron; biasing means for urging the seat plate in a direction protruding from the inside of the groove onto the ground of the apron; , A switch housing member having a substantially closed box shape with an insertion hole formed through the upper surface, an upper end connected to a lower portion of the seat plate, and a lower end connected to the insertion hole.
A moving member extending slidably through the switch housing member and disposed at the bottom of the switch housing member, and detecting that the moving member has approached due to immersion of the seat plate into the groove; And a retractable tubular shield that is installed between the lower portion of the seat plate and the upper surface of the switch housing member at the periphery of the insertion hole, and hermetically covers a portion of the moving member protruding from the switch housing member. Guidance device for an aircraft, comprising: 2. An outer frame, which has an opening that is open above and has a size that does not allow the wheels of the aircraft to be immersed therein, is fitted into the groove, and an outer frame is inserted into the groove so that the seat plate can be protruded and retracted. A switch accommodating member is fixed to the bottom of the frame, and a locking portion protruding toward the center of the opening is formed at the periphery of the opening of the outer frame. 2. The aircraft guidance device according to claim 1, wherein an inclined surface is formed at a central portion of the plate, and the inclined surface is configured to make sealing contact with the locking portion when the seat plate protrudes.