JP5177398B2 - Moving body guide device - Google Patents

Description

  The present invention relates to a moving body guide system, and more particularly to a moving body guide apparatus using light, which is used in a guide system capable of guiding a moving body without using radio waves.

  Conventionally, a guidance system called ILS (Instrument Landing System) has been used to support landing of aircraft such as passenger planes at airports around the world.

  In ILS, glide paths, localizers and marker beacons provide information for safe landing on the aircraft.

  The glide path shows the proper (safe) descent angle to the runway. The localizer indicates the proper (safe) approach direction to the runway. Marker beacons (outer marker, middle marker, inner marker) indicate the distance to the runway.

  Among these, the glide path and the localizer are schematically shown in FIG. Referring to FIG. 1, a conventional ILS 20 generates two radio waves 24 and 26 (not shown) that are directed from the vicinity of an end of an airport runway 22 to the direction and angle at which an aircraft 28 enters. Including equipment. Among these, the radio wave 24 is modulated by a 150 Hz signal, and the radio wave 26 is modulated by a 90 Hz signal. When viewed from the aircraft 28, the radio wave 24 is directed to the right and upward from the radio wave 26. Conversely, the radio wave 26 is directed to the left side and downward from the radio wave 24.

  The output powers of the radio waves 26 and 28 are set to be the same. As a result, at an intermediate position between the direction in which the radio wave 24 is directed and the direction in which the radio wave 26 is directed (in the middle between the top and bottom and the left and right), the signal levels received by the aircraft 28 are equal in both. The control system provided in the aircraft 28 measures the signal levels of both, and indicates the safe traveling direction of the aircraft 28 by a display method called a cross pointer so that the signal levels of both are equal in the vertical and horizontal directions.

  By doing so, as shown in FIGS. 1A and 1B, the aircraft 28 travels on a path 30 intermediate between the direction in which the radio wave 24 is directed and the direction in which the radio wave 26 is directed. At a safe angle, you can proceed to a safe approach to the airport runway 22. This path 30 is called a glide path when viewed from the side, and a localizer when viewed from above.

ILS is used in almost all airports, and Patent Document 1 is a related prior art document.
JP 2006-107177 A

  ILS uses radio waves, and has an advantage that an aircraft can be safely guided to a runway even in a situation where visibility is not good. However, conversely, since radio waves are used, there is a major drawback that maintenance of the transmitter is necessary. In the case of a normal airport, maintenance of the apparatus for ILS is performed at enormous cost. However, in the future, when landing on the moon or docking to a space station installed in orbit, the cost for such a device will be enormous, and in order to reduce the maintenance cost, There is a problem that the reliability must be dramatically increased, and as a result, the cost of the apparatus itself increases.

  Furthermore, there is a problem that electric power is required to use radio waves. Even if there is a private power generation facility at the time of a power failure, there is a possibility that an accident may occur when the power is switched at the time of the power failure, and the function of the airport itself may have to be stopped if the power failure is prolonged. In addition to any accident or disaster as a cause of a power outage, the possibility of intentional destructive activities cannot be excluded.

  In addition, in systems using radio waves, especially when there are high-rise buildings near the airport, there are many cases where ghosts are generated in radio waves received by aircraft, and it is difficult to perform safe guidance. . Unlike in the past, airports and urban areas are now close together, and these problems should become more serious in the future.

  In order to realize safe air transportation, such problems should be tackled nationally.

  As airport landing guidance systems, there are MLS (Microwave Landing System) and LDA (Localizer Type Directional Aids) systems in addition to ILS, but these problems also exist in common. Therefore, there is an urgent need to develop a landing guidance system that solves the above problems. However, the technique described in Patent Document 1 is based on the assumption that radio waves are used, and such a problem cannot be solved.

  These problems are not limited to aircraft. As already mentioned, the same problem can arise with spacecraft guidance, and the same applies to the guidance of moving bodies that do not have a fixed trajectory, such as vehicles traveling on the ground and ships navigating at sea. I can say that. Particularly in the case of automobiles, it is considered to use inter-vehicle communication using radio waves in order to prevent accidents, but the maintenance of the instrument for that purpose is still expensive. In other words, the above-described problem can occur for all of the guidance systems for moving objects.

  SUMMARY OF THE INVENTION Therefore, an object of the present invention is to provide a moving body guide apparatus that can be realized at low cost and can safely guide a moving body.

  Another object of the present invention is to provide a moving body guide apparatus that can reduce the maintenance cost and can guide the moving body safely.

  A moving body guide apparatus according to a first aspect of the present invention is a moving body guide apparatus for guiding a moving body, and is combined with a base block having a main surface and at right angles so as to form a ridgeline. A first reflecting device having two reflecting surfaces, and a ridge line being in the first orthogonal plane with respect to the main surface, and the two reflecting surfaces being symmetrical about the first orthogonal plane, First support means for supporting the first reflecting device on the base block, wherein the first support means has an absolute value of an angle formed by a perpendicular to the main surface and a ridge line of greater than 0 degrees and The first reflecting device is supported so that the first value is smaller than 5 degrees.

  When the first reflecting device is provided in this way, for example, when a foundation block is provided in a ground facility or the like so that the main surface coincides with a predetermined reference surface, the reflected light is applied to the reflecting device from the moving body. By examining whether or not it returns, it can be determined which side of the boundary line defined by the first value described above. Based on this information, it is possible to safely guide the moving body along this boundary line or not from one side of the boundary line to the other side. Moreover, no energy source is required for the operation of the moving body guide apparatus, and no maintenance is required because there are no movable parts. As a result, it is possible to provide a moving body guide system and a guide apparatus therefor that can be realized at low cost and can safely guide the moving body.

  Preferably, the moving body guide device further includes a second reflecting device having two reflecting surfaces combined at right angles to each other so as to form a ridgeline, and a ridgeline of the second reflecting device is a second orthogonal to the main surface. A second for supporting the second reflecting device on the base block so that it is in-plane and the two reflecting surfaces of the second reflecting device are symmetrical with respect to the second orthogonal surface. The second support means has an absolute value of an angle formed between a perpendicular to the main surface and a ridge line of the second reflector, which is greater than 0 degree and less than 5 degrees, and the first support means. The second reflection device is supported so as to have a second value different from the first value.

  When the second reflection device is further provided in this way, the space can be divided into three by the boundary line defined by the first value and the boundary line defined by the second value. Using this information, for example, the moving body can be guided so that the moving body exists inside only one of these three areas and does not go outside. The area that can be guided can be made narrower. Maintenance costs are also very low. As a result, it is possible to provide a moving body guide system and a guide device therefor, which can reduce the maintenance cost and can safely guide the moving body.

  More preferably, the moving body guide device further includes a third reflecting device having two reflecting surfaces combined at right angles to each other so as to form a ridgeline, and a ridgeline of the third reflecting device is a third reflecting surface with respect to the main surface. A third for supporting the third reflecting device on the base block so as to be in the orthogonal plane and so that the two mirror surfaces of the third reflecting device are symmetrical with respect to the third orthogonal surface. The third support means includes a third reflection device such that an absolute value of an angle formed between a perpendicular to the main surface and a ridge line of the third reflection device is a second value. Support.

More preferably, the third support means further supports the third reflection device so that the third reflection device is plane-symmetric with the second reflection device with respect to the first orthogonal plane. The means and the third reflecting means are arranged on the left and right with the first reflecting means as the center, and the limit angles at which they reflect the incident light are equal to each other. The pattern of the reflected light at the time becomes easy to understand, and the moving body can be guided more safely.

  The moving body guide device further includes a second reflector having two mirror surfaces combined at right angles to each other so as to form a ridgeline, and the ridgeline of the second reflector is in the first orthogonal plane, And the second reflecting device is perpendicular to both the main surface and the first orthogonal surface so that the two mirror surfaces of the second reflecting device are symmetrical with respect to the first orthogonal surface. And a second support means for supporting the second reflecting device on the base block so as to be plane-symmetric with the first reflecting device.

  Preferably, the mobile body guide device is a combination of the two mobile body guide devices back-to-back so that the main surfaces of the mutual base blocks are the same surface.

  More preferably, the reflection device belonging to one of the two mobile body guide devices is provided with a light transmissive filter of a different color, and the reflection device belonging to the other mobile body guide device. The device is provided with a light transmissive filter of the same color as the filter of the reflecting device attached to the main surface at the same angle, each belonging to one of the moving body guide devices.

  More preferably, the reflecting device is provided with light transmissive filters of different colors.

  The first reflective device is provided with a first color light transmissive filter, and the second and third reflective devices are provided with a second color light transmissive filter different from the first color. It may be done.

A moving body guide apparatus according to a second aspect of the present invention is a reflecting apparatus that has two reflecting surfaces that are combined at right angles to form a ridgeline and are symmetrical with respect to a predetermined symmetry plane that includes the ridgeline. When mounting only is this reflecting device includes at least reflecting ridgeline direction parallel a length of the device is adjustable, and desired by the reflection device fixable length to the length adjustment device.

  FIG. 2 shows a schematic configuration of a guidance system 50 according to an embodiment of the present invention. This embodiment is for providing the aircraft 80 with information on the safe approach direction and approach angle to the runway 60. In the following drawings and description, the same components are denoted by the same reference numerals. Their names and functions are also the same. Therefore, detailed description thereof will not be repeated.

  Referring to FIG. 2, the guide system 50 is installed in the vicinity of both end portions of the runway 60 so as to face the runway 60, and two reflecting surfaces combined at right angles so as to form a ridgeline. Approach angle guiding devices 62 and 64 using a reflection device (hereinafter referred to as “parallel reflection device”) that reflects only light incident parallel to a predetermined surface to the light source side. An approach direction guide device 66, 68, 70 and 72 using a parallel reflector, installed near both sides of both ends of the runway 60 and facing the direction of the aircraft 80 about to enter the runway 60; And a plurality of retroreflective devices 74 and 76 arranged at regular intervals on both sides of the runway 60.

  As shown in FIG. 2 (B), the approach angle guiding device 62 has an approach line 90 that is generally 3 degrees with respect to the horizontal line, and an upper limit that is 0.5 degrees above and below that, which is a safe approach angle. When the aircraft 80 exists at any one of the three angles of 92 and the lower limit 94, the light from the aircraft 80 is reflected toward the aircraft 80, and in other cases, the light is reflected in the other directions. Has the ability to reflect. The function of the approach angle guide device 64 is also the same.

  FIG. 3 is a perspective view schematically showing the approach angle guide device 62. Referring to FIG. 3, the approach angle guiding device 62 has a flat rectangular parallelepiped base block 100 having a main surface 110 and a lower surface (not shown) parallel to each other, and the main surface 110 of the base block 100. It includes three fixed parallel reflectors 102, 104 and 106. The parallel reflectors 102, 104, and 106 are exactly the same as each other, but the angles that are attached to the base block 100 by the columns 122, 124, and 126, respectively, and the light-transmitting filters that are affixed to the respective front surfaces. Are different from each other in terms of color.

  Each of the parallel reflection devices 102, 104, and 106 includes two mirror surfaces combined so as to form a ridgeline at right angles to each other. In such a parallel reflector, light incident from a direction parallel to a plane perpendicular to both of these mirror surfaces is reflected in that direction, and light incident from other directions is reflected in another direction. It is not reflected on the light source side. The back surface of the mirror surface (the surface facing the outside) is painted so as not to transmit light.

  In the present embodiment, filters of three colors of blue, yellow, and red are provided on the front surfaces of the parallel reflection devices 102, 104, and 106, respectively.

  In FIG. 3, the support column 122 is provided so as to be in a plane that is orthogonal to the main surface 110 and that includes a line of intersection of two mirror surfaces constituting the parallel reflection device 102. Such a surface is hereinafter referred to as a “center plane” of the parallel reflection device 102. As a result, the column 122 supports the parallel reflection device 102 so that the two mirror surfaces constituting the parallel reflection device 102 are symmetrical with respect to the above-described center plane. The same applies to the columns 124 and 126 of the parallel reflectors 104 and 106. However, the mounting method of the parallel reflectors 104 and 106 is different from that of the parallel reflector 102 in that the angles formed by the ridge lines supported by these columns with the main surface 110 are 3.5 degrees and 2.5 degrees, respectively. ing.

  As is clear from the above description, the parallel reflection device 102 reflects only incident light from an elevation angle of 3 degrees to the light source side, and the parallel reflection device 104 reflects only incident light from an elevation angle of 2.5 degrees to the light source side. The parallel reflection device 106 reflects only incident light having an elevation angle of 3.5 degrees toward the light source. Light incident at an angle other than these is reflected in an irrelevant direction and is not reflected on the light source side.

  FIG. 4 is a plan view of the approach angle guide device 62. 5A is a side view of the approach angle guide device 62 as viewed from the direction indicated by the one-dot chain line 5A in FIG. 4, and FIG. 5B is a cross-sectional view at the section indicated by the one-dot chain line 5B in FIG. (C) is a cross-sectional view taken along the dashed line 5C in FIG. In FIGS. 5A and 5B, the parallel reflection device 102 and the parallel reflection device 104 existing behind are not shown for the sake of clarity.

  Referring to FIGS. 4 and 5B, parallel reflection device 102 has a ridgeline (corresponding to the back of the intersecting line of two mirror surfaces constituting parallel reflection device 102) three degrees from the perpendicular to main surface 110. Only the main surface 110 of the foundation block 100 is fixed by the support column 122 so as to be inclined rearward. Therefore, as shown in FIG. 5B, the upper surface of the parallel reflection device 102 faces 3 degrees above the horizontal line (assuming that the base block 100 is fixed to the ground so that the main surface 110 is horizontal). That is, the parallel reflection device 102 reflects light incident from a direction facing upward 3 degrees from the horizontal position in that direction, and does not reflect light incident from other directions to the light source side, but in another direction. reflect.

  Similarly, referring to FIG. 4 and FIG. 5A, the parallel reflector 106 includes the base block 100 by the support 126 so that the ridgeline thereof is inclined backward by 2.5 degrees from the position perpendicular to the main surface 110. The main surface 110 is fixed. As a result, the parallel reflection device 106 reflects light incident from a direction with an elevation angle of 2.5 degrees in that direction. Light incident from other directions is reflected in another direction and is not reflected on the light source side.

  Referring to FIGS. 4 and 5C, the parallel reflection device 104 has the main surface of the base block 100 by the support column 124 so that the ridgeline thereof is inclined backward by 3.5 degrees from the position perpendicular to the main surface 110. 110 is fixed. Therefore, the upper surface of the parallel reflection device 104 faces 3.5 degrees above the horizontal line as shown in FIG. As a result, the parallel reflection device 104 reflects light incident from a direction with an elevation angle of 3.5 degrees in that direction, and does not reflect light incident from other directions.

  For example, it is assumed that the incident light 128 to the parallel reflection device 102 shown in FIG. 5B enters in a plane with an elevation angle of 3 degrees. Then, this light is reflected by the two reflecting surfaces of the parallel reflection device 102 and reflected to the light source side. On the other hand, in the case of incident light 129 incident from a surface with an elevation angle other than 3 degrees, as shown in FIG. 5B, it is reflected in a direction different from the light source and does not return to the light source.

The same applies to the parallel reflection devices 104 and 106.
The configuration of the approach angle guide device 62 described above is summarized as follows. Referring to FIG. 4, for example, the parallel reflection device 102 has one ridge line obtained by combining two reflection surfaces at right angles to each other. In the support column 122, the two mirror surfaces are symmetrical with respect to the orthogonal plane (the central plane of the parallel reflection device 102) so that the ridge line is in the plane orthogonal to the main surface 110 and as is apparent from FIG. Thus, the parallel reflection device 102 is supported by the basic block. The column 122 supports the parallel reflection device 102 so that the absolute value of the angle formed by the main surface 110 and the ridgeline 108 (see FIG. 5B) is 3 degrees.

  According to the approach angle guide device 62 configured in this way, when the aircraft 80 turns on the light that illuminates the front when landing, the reflected light from the approach angle guide device 62 appears to the aircraft 80 as follows. become.

  When the aircraft 80 is above the upper limit 92 shown in FIG. 2 (B), the light from the aircraft 80 is incident on the approach angle guide device 62 at different angles of 3.5 degrees, 3 degrees, and 2.5 degrees. Therefore, the direction of reflected light from the parallel reflection device 102, the parallel reflection device 104, and the parallel reflection device 106 is different from the direction of the aircraft 80. As a result, no light is reflected from the approach angle guide device 62 to the aircraft 80.

  When the aircraft 80 is positioned at the elevation angle of the upper limit 92, the light from the aircraft 80 is reflected only by the parallel reflection device 104 and returns to the direction of the aircraft 80. The reflected light from the parallel reflector 102 and the parallel reflector 106 does not return to the aircraft 80. As a result, only one reflected light can be seen from the aircraft 80. The light returning to the aircraft 80 is yellow because it comes from the parallel reflector 104.

  When the aircraft 80 is between the approach line 90 and the lower limit 94, the angle of incident light from the aircraft 80 to the parallel reflectors 102, 104, and 106 is either 3.5 degrees, 3 degrees, or 2.5 degrees. Therefore, the reflected light from these does not return to the aircraft 80. Therefore, the reflected light cannot be seen from the aircraft 80.

  When the aircraft 80 is located on the approach line 90, the light from the aircraft 80 is reflected only by the parallel reflector 102 and returns in the direction of the aircraft 80. Reflected light from the parallel reflector 104 and the parallel reflector 106 does not return to the aircraft 80. As a result, only one reflected light can be seen from the aircraft 80. Since this is due to the parallel reflection device 102, it is blue.

  When the aircraft 80 is at a position between the approach line 90 and the lower limit 94, the angles of incident light from the aircraft 80 to the parallel reflectors 102, 104, and 106 are 3.5 degrees, 3 degrees, and 2.5 degrees. Therefore, the reflected light from these does not return to the aircraft 80. Therefore, the reflected light cannot be seen from the aircraft 80.

  When the aircraft 80 is positioned on the lower limit 94, the light from the aircraft 80 is reflected only by the parallel reflector 102 and returns in the direction of the aircraft 80. Reflected light from the parallel reflector 104 and the parallel reflector 106 does not return to the aircraft 80. As a result, only one reflected light can be seen from the aircraft 80. Since this is due to the parallel reflection device 102, it is blue.

  When the aircraft 80 is at a position below the lower limit 94, the angle of incident light from the aircraft 80 to the parallel reflectors 102, 104, and 106 is different from any of 3.5 degrees, 3 degrees, and 2.5 degrees. Therefore, the reflected light from these does not return to the aircraft 80. Therefore, the reflected light cannot be seen from the aircraft 80.

  From the above, it can be seen that when the aircraft 80 enters the runway 60 at such an angle that the blue reflected light can always be seen from the approach angle guide device 62, it is safe to descend. If you can't see the reflected light and see the yellow reflected light, you know that the altitude is too high. If the red reflected light cools, the altitude is too low to be dangerous. The aircraft 80 can automatically land by capturing the reflected light with a camera and converting it into an electrical signal. Alternatively, the pilot can land in the visual field by displaying the image of the reflected light captured by the camera on the monitor in the cockpit. At this time, the approach angle can be confirmed more reliably by considering the colors of these reflected lights.

  In the present embodiment, the light beam irradiated at the time of landing in the aircraft 80 is white light, and although the irradiation range is narrowed, it has a certain spread, so that the light from the aircraft 80 is reflected by the parallel reflection device 102. , 104 and 106, the reflected light reliably reaches the aircraft 80 if the approach angle is any of 3.5 degrees, 3 degrees, and 2.5 degrees.

  Next, an approach direction guide device 66 shown in FIG. 2A for guiding the aircraft 80 to the correct approach direction to the runway 60 will be described. The other approach direction guide devices 68, 70, 72 shown in FIG.

  Referring to FIG. 6, the approach direction guide device 66 uses a parallel reflection device in the same manner as the approach angle guide device 62 shown in FIG. 3, and the guidance method is the same as that of the approach angle guide device 62. However, here, in order to indicate the approach direction rather than the approach angle to the approach direction guide device 66, the configuration is as shown in FIG. Hereinafter, the configuration of the approach direction guide device 66 will be described.

  Referring to FIG. 6, the approach direction guide device 66 includes a bottom surface 136 and a base block having three side walls 160, 162, and 164 provided so as to be orthogonal to each other and perpendicular to the bottom surface 136. 130 and a parallel reflector 140 attached to the inner side surface 134 of the side wall 160 of the foundation block 130 so that the ridgeline 144 is parallel to the upper surface of the bottom surface 136. Since the upper surface and the lower surface (not shown) of the bottom surface 136 are parallel to each other and the bottom surface 136 is fixed to the ground so that the upper surface thereof is horizontal, the ridgeline 144 of the parallel reflector 140 is also horizontal. In the present embodiment, the inner surface 138 of the side wall 164 is the main surface.

  FIG. 7 is a plan view of the approach direction guide device 66 shown in FIG. Referring to FIG. 7, the parallel reflection device 140 is configured so that the ridgeline 144 is horizontal and the angle between the ridgeline 144 and the surface 134 is a predetermined angle α from the vertical line with respect to the surface 134. It fixes to the surface 134 so that it may incline to the opening side. Therefore, the mirror surface of the parallel reflection device 140 is inclined by the same angle with respect to the surface 134. As a result, as indicated by a line 150, light incident on the parallel reflection device 140 from a surface that is not perpendicular to the two mirror surfaces of the parallel reflection device 140 is not reflected on the light source side but is reflected in another direction. On the other hand, the light incident on the approach direction guide device 66 in a plane perpendicular to the two mirror surfaces (surface orthogonal to the ridge line 144) as shown by the line 152 is sequentially reflected by the two mirror surfaces of the parallel reflection device 140, Reflected to the light source side in the same plane as the incident light.

  Therefore, when the aircraft is in a plane orthogonal to the two mirror surfaces of the approach direction guide device 66, the light from the aircraft is reflected by the parallel reflection device 140 and returns to the direction of the aircraft. When there is an aircraft, light from the aircraft is not reflected by the parallel reflection device 140 and returned to the aircraft. The approach direction guide device 66 is installed on the ground so that the outer side surface of the side wall 164 of the approach direction guide device 66 is parallel to the side of the runway and the bottom surface 136 is horizontal, and a safe traveling angle is obtained. The angle α is determined so as to be the limit position. Then, when the reflected light from the approach direction guide device 66 is seen by the aircraft, it is understood that the aircraft is traveling in a safe approach direction. That is, the aircraft changes the traveling direction to a position where the reflected light from the approach direction guide device 66 can be seen, and then adjusts the traveling direction so that the reflected light can be continuously viewed, thereby moving the aircraft in a safe approach direction. be able to. If the runway reaches a position where it can be seen, landing can be attempted with the retroreflective devices 74 and 76 arranged on both sides of the runway as targets. The angle α only needs to be larger than 0 degree, but if it is too large, the meaning as the direction guide device is lost. On the other hand, in the presence of crosswinds, when the aircraft is landing, it is necessary to point the nose slightly toward the windward side. Therefore, it is necessary to allow a certain amount of allowance in consideration of the spread of lighting. Nevertheless, it is considered practically sufficient to cover up to about 30 degrees. Therefore, it may be 0 degrees <α <30 degrees.

  The configuration of the approach direction guide device 66 described above is summarized as follows. The parallel reflection device 140 has two reflecting surfaces combined at right angles to each other so as to form one ridge line. The column 148 is parallel-reflected so that the ridge 144 is in a plane orthogonal to the inner surface 132 and the two mirror surfaces constituting the parallel-reflecting device 140 are symmetrical with respect to the center plane of the parallel-reflecting device 140. The device 140 is supported on the base block 130. Further, as shown in FIG. 7, the support column 148 supports the parallel reflection device 140 so that the absolute value of the angle formed between the perpendicular to the inner side surfaces 134 and 138 and the ridgeline 144 is α. In other words, the support column 148 supports the parallel reflection device 140 so that the absolute value of the angle formed by the surfaces 134 and 138 and the perpendicular line 149 to the ridge line 144 is α. This also means that the support column 148 supports the parallel reflection device 140 so that the absolute value of the angle formed by the ridge line 144 and the inner surface 132 is α.

  Therefore, as shown in FIG. 2 (A), for example, the bottom surface of the base block 130 is horizontal and from the aircraft side so that the outer surface of the side wall 164 is parallel to the side of the runway. When the approach direction guide device 66 is installed on the right side, and the approach direction guide device 68 that is in a mirror image relationship with the approach direction guide device 66 is installed on the left side, the limit portions on both sides of the safe approach direction to the runway are set on the aircraft. Can be easily confirmed.

As a light source for light emitted from the aircraft to the approach angle guide device 62, the approach direction guide device 66, etc., if a light for ground irradiation that is turned on at the time of landing is used, it is not necessary to provide a light source independently. However, in this case, since the light returns to the vicinity of the light source due to the nature of the parallel reflection device, it is necessary to install a camera for measuring the reflected light near the light source. Light source in the case such as that kicked attached to the landing gear is also that you the structure of landing gear is complicated. In order to solve such a problem, as shown in FIG. 8, a light source for irradiating a predetermined direction and a camera for photographing reflected light from the approach angle guide device 62 are provided on the lower surface of the nose of the aircraft 170. A combined measuring device 172 may be provided.

[Operation]
In the guidance system 50 described above, the aircraft is guided as follows.

  As is apparent from the description of the configuration with reference to FIG. 9A, the approach direction guide devices 66 and 68 are disposed on both sides of the end portion of the runway 60, and both have a mirror image structure. Assume a case. Then, the position where the approach direction guiding device 66 reflects light, that is, the limit of the safe approach direction is indicated by a line 82, for example. On the other hand, the position where the approach direction guide device 68 reflects light is indicated by a line 84 that is symmetrical with respect to the line 82 about the center line of the runway 60.

  As shown in FIG. 9A, even if light is emitted from the aircraft 200 in the region 210 outside the line 82 (upper side in FIG. 9A) toward the approach direction guide device 68, the reflected light is not reflected in the aircraft. I will not return to 200. Therefore, it can be seen that the aircraft 200 is not in a safe traveling direction. The same applies when the aircraft is in the region 212 outside the line 84 (the lower side in FIG. 9).

  When the aircraft 80 reaches the plane indicated by the line 82 and the nose faces the direction of the approach direction guide device 66, the reflected light from the approach direction guide device 66 reaches the aircraft 80. The aircraft 80 can determine that the aircraft 80 is traveling in a safe approach direction by detecting this light. The same applies when the aircraft 80 reaches the plane indicated by the line 84.

  On the other hand, even if light is irradiated from the aircraft 80 in the region sandwiched between the lines 82 and 84 toward the approach direction guide devices 66 and 68, the light is not reflected and the reflected light does not reach the aircraft 80. . Therefore, once the aircraft 80 enters this position, the aircraft 80 may adjust its traveling direction so that neither the reflected light from the approach direction guide device 66 nor the reflected light from the approach direction guide device 68 is received.

  On the other hand, the approach angle guidance is performed as follows. Referring to FIG. 9B, the region where the parallel reflection device 104 (see FIGS. 3 to 5) of the approach angle guiding device 62 reflects light is the upper limit 92 position, and the parallel reflection device 106 transmits light. Assume that the reflective region is indicated by a lower limit 94. The reflected light of the light irradiated by itself does not reach the aircraft 230 in the region 240 above the upper limit 92 at all. Thus, aircraft 230 knows that it is outside the safe approach angle range. On the other hand, no reflected light returns to the aircraft 232 in the region 242 below the lower limit 94. Thus, aircraft 232 knows that he is outside the safe approach angle range.

  When the aircraft 230 enters an attitude as shown by the upper limit 92, yellow reflected light from the approach angle guide device 62 reaches the aircraft 230. Thus, it can be seen that aircraft 230 has reached the upper end of the safe approach angle range. Further, when the approach angle of the aircraft 230 becomes smaller and reaches the position indicated by the aircraft 80, the yellow reflected light from the approach angle guiding device 62 disappears and the blue reflected light becomes visible. If the aircraft 80 is lowered at an approach angle such that the blue reflected light can be seen, the aircraft 80 has advanced a safe approach angle with respect to the runway 60.

  On the other hand, when the aircraft 232 attempts to enter the runway 60 at a descending speed as indicated by the lower limit 94, the aircraft 232 can see the reflected light from the parallel reflector 106. This light is red. As a result, it can be seen that the aircraft 80 is at the lower limit of the approach angle region determined by the safe descent angle. Therefore, it is understood that it is necessary to increase the altitude a little and increase the approach angle.

  In this way, by irradiating light to the approach angle guide device 62 and the approach direction guide devices 66 and 68 from the aircraft about to land on the runway 60, the presence or absence of the reflected light and the color of the reflected light are determined. It is possible to determine whether the approach direction and the approach angle of the aircraft are in a safe area. This principle allows the aircraft to be able to enter the runway 60 with a safe approach direction and altitude, either manually by visual inspection of the pilot, or automatically by electronically determining the presence and color of reflected light. You can steer.

  Note that a plurality of retroreflective devices 74 and 76 are arranged at regular intervals on both sides of the runway 60 as described above (see FIG. 2A). As the name suggests, they have a function of reflecting incident light in any direction. Therefore, it is possible to confirm the position of the runway 60 by light from these, and land safely. In this case, in order to distinguish the reflected light from these and the reflected light from the approach angle guide device 62 and the approach direction guide device 66, the approach angle guide device 62 and the approach direction guide device 66 have different colors. It is desirable to provide a filter.

  Furthermore, in the said embodiment, the parallel reflection apparatus is being fixed to the basic block using the support | pillar. However, the present invention is not limited to such an embodiment. For example, the ridge line 144 may be directly bonded to an adjacent surface with a predetermined angle. Alternatively, a stay that supports the parallel reflection device may be provided so that the posture of the parallel reflection device 140 becomes a desired one.

  In addition, for the approach angle guide device 62 and the approach angle guide device 64 at the opposite end of the runway 60, the colors of the films attached to the individual parallel reflection devices may be different in order to distinguish each other. . The same applies to the approach direction guide devices 66, 68, 70 and 72.

  If the guide device is realized using the parallel reflection device in this way, the following effects can be obtained. First, the parallel reflector is a completely passive device with no moving parts and no power. Therefore, it is not necessary to perform maintenance, and it is not necessary to supply power for operation. The cost required for operation is almost zero. In the case of the above-described usage method, the accuracy of retroreflection of the parallel reflection device may be low. Therefore, for example, a parallel reflection device can be easily realized by combining two reflecting mirrors at right angles to each other, and the cost can be kept low. However, it is a matter of course that a more accurate one such as a prism may be used instead of a combination of two reflecting mirrors.

  In the said embodiment, the parallel reflection apparatus is arrange | positioned facing the substantially the same direction mutually. However, in the case of an airport, there is a possibility of using the runway in the reverse direction depending on the wind direction. For such a case, for example, two devices shown in FIG. 3 or FIG. 6 are arranged at the end of the runway in a back-to-back manner, that is, in such a way that the direction in which the parallel reflection device faces is opposite. The process performed by the aircraft is the same whether the runway is used in either direction.

  FIG. 10 shows such an approach angle guide device 260. Referring to FIG. 10, this approach angle guiding device 260 divides the upper surface of the bottom block 270 into a first surface 280 and a second surface 282 at the center of the upper surface of the bottom block 270 and the bottom block 270. And a parallel reflection device 102, 104 and 106 provided on the first surface 280 in the same order and installation manner as the parallel reflection devices 102, 104 and 106 shown in FIG. Parallel reflectors 292, 294 provided on the second surface 282 in an order and installation form that are point-symmetrical with respect to the center of the partition member 272 with respect to the arrangement of the parallel reflectors 102, 104, and 106, and 296. The ridgelines of the parallel reflectors 292, 294, and 296 are similar to the parallel reflectors 102, 104, and 106, respectively, and are inclined by 3 degrees, 3.5 degrees, and 2.5 degrees, respectively, with respect to the normal of the second surface 282. ing. Further, blue, yellow, and red filters are installed on the front surfaces of the parallel reflection devices 292, 294, and 296, respectively, as with the parallel reflection devices 102, 104, and 106.

The approach angle guide device 260 shown in FIG. 10 has the same configuration as a combination of the two approach angle guide devices 62 shown in FIG. 3 so that the main surfaces 110 of the foundation blocks 100 are the same. It is.

  The set of parallel reflectors 102, 104, and 106 and the set of parallel reflectors 292, 294, and 296 are arranged back to back, and the installation angle of the parallel reflectors and the color of the filters at the point-symmetric positions are equal to each other. By doing in this way, when the approach angle guiding device 260 is arranged in the vicinity of the runway, the angle and color conditions of the reflected light seen from the aircraft are equal even when the aircraft enters the runway from any direction. As a result, if the approach angle guiding device 260 is installed, it is not necessary to change the arrangement of the approach angle guiding device according to the approach direction of the runway.

  The above-described embodiment is directed to guidance at the time of landing of an aircraft. However, the present invention is not limited to such an embodiment. It will be apparent to those skilled in the art that the present invention can be applied to clearly define the boundary between a safe traveling direction and angle and an unsafe traveling direction and angle in a general mobile guidance system. Let's go. For example, this system can be used to guide or guide a moving body that does not move on a fixed track such as a vehicle and a ship.

  Furthermore, the approach angle guide device 62 of the above embodiment includes three parallel reflectors 102, 104 and 106, and the approach direction guide device 66 includes only one parallel reflector 140, but the present invention. Is not limited to such an embodiment. For example, two parallel reflection devices may be provided. In this case, it is possible to divide the space into three parts and show it to the user by making the angles at which they reflect light different from each other. Further, when three or more parallel reflection devices are used, two of them may have the same angle for reflecting light. When three or more parallel reflection devices are used, the guide device can be easily identified by a pattern in which the parallel reflection devices are arranged.

  FIG. 11 shows such an approach angle guide device 320. Referring to FIG. 11, approach angle guiding device 320 is similar to base block 100 shown in FIG. 3, and has a base block 330 having an upper surface 332, and parallel reflectors 306 arranged on top surface 332 in order from the left in the drawing. , 304, 102, 104 and 106.

  The parallel reflection devices 102, 104 and 106 are the same as those shown in FIG. 3, and only the order of their arrangement is different. Each of the parallel reflectors 102, 104, and 106 is attached to the upper surface 332 at the same angle as that of the main surface 110 in FIG. In addition, blue, yellow, and blue films are respectively provided on the front surfaces.

  The parallel reflection device 306 is the same as the parallel reflection device 106 and is attached to the upper surface 332 at the same angle as the parallel reflection device 106, and the red film is provided on the front surface like the parallel reflection device 106. The parallel reflection device 304 is the same as the parallel reflection device 104, is attached to the upper surface 332 at the same angle as the parallel reflection device 104, and the yellow film is provided on the front surface in the same manner as the parallel reflection device 104.

  In this approach angle guide device 320, it is possible to determine whether or not the approach angle of the aircraft is an appropriate value based on the reflected light from the parallel reflectors 102, 104, 106, 304, and 306, as shown in FIG. Furthermore, since the approach angle guide device 320 is bilaterally symmetric, it is easier to see from the aircraft than the one shown in FIG. 3, and it is also easy to recognize the reflected light pattern by electronic processing.

  In the embodiments described above, each has a basic block, and a parallel reflection device is mounted on the base block at a predetermined angle. By doing in this way, when manufacturing a parallel reflection device at the factory, the mounting angle can be adjusted with a certain degree of accuracy, and multiple parallel reflection devices can be assembled. What is necessary is just to install an apparatus in a desired flat position.

  Note that the material of the foundation block may be appropriately selected depending on the application. For example, when installing in an airport, the foundation block may be concrete. When installing in a space station, it is only necessary to use a light housing and a hollow housing. If a magnet is used, installation can be simplified and stable.

  However, in some cases, the accuracy of the installation angle may not be a problem. In such a case, it is convenient to be able to install the parallel reflection device at an appropriate position while adjusting the angle at the installation site.

  FIG. 12 shows a side view of the approach angle guiding device 350 in which the angle of the parallel reflection device can be adjusted. Referring to FIG. 12, the approach angle guiding device 350 includes a parallel reflecting device 360 having two reflecting surfaces combined at right angles to each other so as to form a ridgeline. The lower sides of the two reflecting surfaces of the parallel reflection device 360 have a shape that is linearly cut from the tip side toward the ridge line side. By setting the lower side of the reflection surface in such a shape, the parallel reflection device 360 naturally faces obliquely upward.

  The approach angle guide device 350 further protects the reflecting surface of the parallel reflecting device 360 and stabilizes the posture of the parallel reflecting device 360, so that the protective member 362 attached to the lower side of the parallel reflecting device 360 and the reflecting surface of the parallel reflecting device 360 It includes a support member 364 having an opening 370 that is hollow and formed in the lower portion of the rear surface, provided in a shape to support the parallel reflection device 360 behind the ridgeline. A circular opening (not shown) is formed on the lower surface of the support member 364. Further, the approach angle guide device 350 is inserted upward from the opening on the lower surface of the support member 364, and an adjustment screw 368 engaged with a female screw (not shown) inside the support member 364, and an adjustment screw 368 in the opening 370. And an adjustment nut 366 for adjusting the installation angle of the approach angle guide device 350 with respect to the ground surface 352 by moving the adjustment screw 368 up and down.

  By rotating the adjustment nut 366, the adjustment screw 368 enters and exits from the lower part of the support member 364. As a result, the length component of the adjustment screw 368 in the direction parallel to the ridgeline of the parallel reflection device 360 changes. By not turning the adjustment nut 366, the adjustment screw can be fixed to the parallel reflection device 360 with a desired length. As a result, the installation angle of the parallel reflection device 360 with respect to the ground surface 352 can be freely adjusted within the range in which the adjustment screw 368 can enter and exit.

  If the mounting angle of the parallel reflection device 360 can be adjusted in this way, the approach angle guide device 350 can be simply installed at a desired angle at a desired location.

  In the above-described embodiment, it is assumed that light incident on the reflecting plate is visible light. However, the present invention is not limited to such an embodiment. When the reflected light is detected not by visual observation but by an electronic device, light other than visible light, for example, far-infrared rays can also be used. When using far-infrared rays, it is possible to detect reflected light relatively clearly even in places with poor visibility due to fog or the like. The detected far-infrared rays can be visualized and displayed on a monitor, etc., and used for manual operation.

  The above-described embodiment is for the case of being used for aircraft guidance at the time of landing of an aircraft at an airport or the like. However, the present invention is not limited to such an embodiment. It can be used not only for airplanes but also for landing on the moon, docking a spacecraft to a space station launched in outer space, and guiding vehicles that can move freely without being bound by orbit. In such a case, the degree to which the parallel reflection device should be installed depends on the application. For example, in the case of a moving body whose posture is predicted to fluctuate greatly, such as a spacecraft or a ship, it is expected that even a relatively large installation angle is required. Therefore, it is preferable to use a plurality of parallel reflection devices.

  The embodiment disclosed herein is merely an example, and the present invention is not limited to the above-described embodiment. The scope of the present invention is indicated by each claim of the claims after taking into account the description of the detailed description of the invention, and all modifications within the meaning and scope equivalent to the wording described therein are included. Including.

It is a figure which shows schematic structure of the conventional ILS20. It is a figure which shows schematic arrangement | positioning of the ground installation in the guidance system 50 which concerns on one embodiment of this invention. It is a perspective view of approach angle guidance device 62 used with guidance system 50 concerning one embodiment of the present invention. It is a top view of the approach angle guide apparatus 62 shown in FIG. It is the side view and side sectional view of the approach angle guide device 62 shown in FIG. It is a perspective view of the approach direction guide apparatus 66 used with the guidance system 50 which concerns on one embodiment of this invention. It is a top view of the approach direction guide apparatus 66 shown in FIG. It is a figure which shows arrangement | positioning of the camera which image | photographs the light provided in an aircraft, and reflected light. It is a figure for demonstrating how a space is divided | segmented by the guidance system 50 which concerns on one embodiment of this invention, and how reflected light is visible from an aircraft. FIG. 10 is a perspective view of an approach angle guide device 260 that is another example of an approach angle guide device that can be used in the guide system 50. FIG. 10 is a perspective view of an approach angle guide device 320 that is still another example of an approach angle guide device that can be used in the guide system 50. It is a side view of the approach angle guide apparatus 350 which can adjust an installation angle at the time of installation.

Explanation of symbols

  50 guidance system, 60 runway, 62, 64, 260, 320, 350 approach angle guide device, 66, 68, 70, 72 approach direction guide device, 80 aircraft, 90 approach line, 92 upper limit, 94 lower limit, 102, 104 , 106, 292, 294, 296, 304, 306, 360 Parallel reflection device.

Claims (10)

A moving body guide device for guiding a moving body,
A foundation block having a main surface;
A first reflective device having two reflective surfaces combined at right angles to each other to form a ridge;
The first reflecting device is the base so that the ridge line is in a first orthogonal plane with respect to the main surface and the two reflecting surfaces are symmetrical with respect to the first orthogonal surface. First support means for supporting the block;
The first support device is configured so that an absolute value of an angle formed between a perpendicular to the main surface and the ridge line is a first value larger than 0 degree and smaller than 30 degrees. Supporting device for moving body. A second reflective device having two reflective surfaces combined at right angles to each other to form a ridgeline;
The ridgeline of the second reflecting device is in a second orthogonal plane with respect to the main surface, and the two reflecting surfaces of the second reflecting device are plane-symmetric about the second orthogonal surface. and so that further comprises a second support means for supporting the second reflecting device to the base block,
In the second support means, an absolute value of an angle formed between a perpendicular to the main surface and the ridge line of the second reflecting device is greater than 0 degree and less than 5 degrees, and the first value The moving body guide device according to claim 1, wherein the second reflecting device is supported so as to have a second value different from the second value. A third reflective device having two reflective surfaces combined at right angles to each other to form a ridge;
The ridgeline of the third reflecting device is in a third orthogonal plane with respect to the main surface, and the two mirror surfaces of the third reflecting device are symmetrical with respect to the third orthogonal plane. And further comprising third support means for supporting the third reflector on the foundation block,
The third support means may be configured so that an absolute value of an angle formed between a perpendicular to the main surface and the ridge line of the third reflector is the second value. The moving body guide apparatus according to claim 2 , which is supported. The third supporting means further supports the third reflecting device such that the third reflecting device is plane-symmetric with the second reflecting device with respect to the first orthogonal plane. 4. A moving body guide apparatus according to 3. A second reflector having two mirror surfaces combined at right angles to each other to form a ridge;
The ridgeline of the second reflecting device is in the first orthogonal plane, and the two mirror surfaces of the second reflecting device are symmetrical with respect to the first orthogonal plane. And the second reflecting device is symmetrical with respect to the first reflecting device with respect to a second orthogonal surface orthogonal to both the main surface and the first orthogonal surface. The moving body guide apparatus according to claim 1, further comprising second support means for supporting a reflecting device on the base block. A mobile body guide device in which the two mobile body guide devices according to claim 2 are combined back to back so that the main surfaces of the mutual base blocks are flush with each other. Of the two moving body guiding devices, the reflecting device belonging to one moving body guiding device is provided with light transmissive films of different colors, and the reflecting device belonging to the other moving body guiding device includes 7. A moving body guide according to claim 6, wherein a light-transmitting film of the same color as a film of a reflecting device attached to the main surface at the same angle is provided. apparatus. The moving body guide apparatus according to any one of claims 2 to 5, wherein different reflective devices are provided with light transmissive films of different colors. The first reflecting device is provided with a light transmissive film of a first color,
The moving body guide apparatus according to claim 4, wherein the second and third reflecting devices are provided with a light transmissive film having a second color different from the first color. A moving body guide device for guiding a moving body,
A reflecting device having two reflecting surfaces which are combined at right angles to form a ridge line and are symmetrical with respect to a predetermined symmetry plane including the ridge line;
The reflection device attached only been in, and at least the reflective said ridge parallel to length of the device is adjustable, and a desired said reflective device fixable length adjustment length device, mobile Guide device.