JP6713696B1 - Landing site and its fence - Google Patents

Abstract

PROBLEM TO BE SOLVED: To reduce the influence of a crosswind at the time of landing of a rotorcraft and to suppress the generation of vortex around the rotor, thereby allowing the rotorcraft to land more safely. SOLUTION: The fence part is installed around a landing point of a rotary wing aircraft, and the fence part prevents wind from flowing into the landing point, and wind is easier than the windbreak part. A landing field characterized by having a passable ventilation part, the ventilation part being provided under the windbreak part, and a fence part thereof, and a landing site of a rotorcraft. And a floor part installed at the landing point, the fence part has a windbreak part that inhibits the inflow of wind to the landing point, and the floor has wind. This is solved by a landing site that is characterized by the formation of ventilation openings that can pass vertically. [Selection diagram] Figure 1

Description

The present invention relates to takeoff and landing equipment for rotary wing aircraft.

Patent Document 1 below discloses a heliport in which the surroundings of a departure/arrival base are surrounded by walls. The following Patent Document 2 discloses a heliport that allows downwash of a helicopter to escape to the underfloor.

Japanese Unexamined Patent Publication No. 1-24905 Japanese Patent Laid-Open No. 5-195515

In recent years, application of unmanned aerial vehicles to various businesses has been studied. Among unmanned aerial vehicles, small multicopters, which are currently the mainstream, have a smaller body weight than manned helicopters and are easily affected by crosswinds. If the multicopter is exposed to a strong crosswind near the surface of the ground, the crosswind may disturb the horizon of the aircraft, resulting in failure to land. On the other hand, if the landing area is surrounded by a wall in order to suppress the effect of crosswind, a vortex ring is generated around the rotor of the multicopter due to the upwash flow of the wall in addition to the ground effect due to downwash. It may become easier and the attitude control of the machine may become unstable.

In view of such a problem, the problem to be solved by the present invention is to reduce the influence of crosswind at the time of landing of a rotorcraft, suppress the occurrence of vortex around the rotor, and make the rotorcraft lander more safely. Especially.

In order to solve the above problems, the landing field of the present invention includes a fence portion installed around a landing point of a rotorcraft, and the fence portion is a windbreak unit that inhibits the inflow of wind to the landing point. And a ventilation part through which wind can pass more easily than the wind protection part, and the ventilation part is provided below the wind protection part.

In the landing field of the present invention, the fence part installed around the landing point of the rotary wing aircraft is provided with a windbreak part that blocks the inflow of wind to the landing site, and a wind below the windbreak part rather than the windbreak part. Has a ventilation part that allows easy passage. The windbreak of the fence is a wall that protects the rotorcraft from crosswinds. The ventilation section of the fence section suppresses the generation of vortex by discharging the downwash of the rotorcraft to the outside of the landing site. This stabilizes the attitude of the rotorcraft during landing and enables the rotorcraft to land more safely.

Further, in order to solve the above problems, the landing field of the present invention includes a fence portion installed around the landing point of the rotorcraft and a floor portion installed at the landing point, and the fence part is The gist of the present invention is that it has a windbreak part that blocks the inflow of wind to the landing point, and that the floor has a ventilation port through which the wind can pass vertically.

In the landing field of the present invention, the fence portion installed around the landing point of the rotorcraft includes a windbreak part that inhibits the inflow of wind to the landing point, and the floor part installed at the landing point is protected from wind. Ventilation openings are formed so that it can pass vertically. The windbreak of the fence is a wall that protects the rotorcraft from crosswinds. The ventilation openings on the floor allow the downwash of the rotorcraft to pass under the floor to land the rotorcraft at a position higher than the surface of the ground, reducing the effect of the ground effect during landing and vortexing. Can be suppressed. This stabilizes the attitude of the rotorcraft during landing and enables the rotorcraft to land more safely.

Further, in the landing field of the present invention, the floor portion has a grid-like floor surface, the floor portion is supported by a plurality of columns installed in the landing site, the vertical direction of the fence portion It is preferable that a ventilation portion is provided below the floor surface so that wind can easily pass through the windproof portion. The downwash of the rotorcraft is discharged from the ventilation section to the outside of the landing site, so that the vortex can be more reliably prevented.

Further, in the landing site of the present invention, it is preferable that the windproof portion has a vertical width of 60 cm or more, and the ventilation portion has a vertical width of 15 cm or more. This is because the windbreak part needs to have a width that can block the crosswind, and the ventilation part needs a width that allows the downwash to be smoothly discharged to the outside of the landing site.

Further, in the landing field of the present invention, it is preferable that the ventilation part is a mesh fence. By configuring the ventilation part with a mesh fence, it is possible to prevent animals and the like from entering the landing site from the ventilation part.

Further, in the landing field of the present invention, it is preferable that the windbreak part has a window part in which a part of the wall surface is cut out or a see-through part made of a light-transmitting material. By providing a window part and a see-through part in the windshield that allow the inside of the landing field to be viewed from outside the landing site, it becomes possible to land the rotorcraft while checking the condition of the rotorcraft.

In addition, in the landing field of the present invention, it is preferable that a rectifying unit that allows wind to easily pass therethrough is provided at the upper end of the windbreak unit and in the vicinity of the windbreak unit. When the cross wind is blocked by the windbreak portion, a turbulent flow is generated near the upper end of the windbreak portion due to the difference in wind speed caused thereby. Turbulence can adversely affect attitude control of rotorcraft. By providing a rectifying section at the upper end of the windbreak section and in the vicinity thereof to allow the wind to pass through more easily than other parts of the windbreak section, the difference in wind speed near the top end of the windbreak section is reduced, and turbulence is moderated. be able to. At this time, it is preferable that the rectifying unit is a mesh, a lattice, or a horizontal plate with a gap gradually increasing toward the upper end.

Further, in the landing field of the present invention, it is preferable that the area of the landing point surrounded by the fence portion is 100 m ² or less. In the landing field of the present invention, the smaller the area of the landing point, the more remarkable the effect of stabilizing the posture by the ventilation section.

At this time, it is preferable that the rotary wing aircraft is an unmanned rotary wing aircraft that can be operated from outside. Unmanned aerial vehicles have a smaller body weight than manned aircraft and are more prone to crosswinds. According to the landing field of the present invention, such an unmanned aerial vehicle can be landed more safely.

In order to solve the above-mentioned subject, the fence part of the present invention is used for the landing field of the present invention.

As described above, according to the landing field and the fence portion thereof of the present invention, the influence of the crosswind at the time of landing of the rotorcraft is reduced, the generation of vortex around the rotor is suppressed, and the rotorcraft is landed more safely. It becomes possible.

FIG. 3 is a schematic perspective view of a landing field according to the first embodiment. It is a schematic diagram explaining the difference of the air flow around a rotor by the presence or absence of a ventilation part. It is a schematic perspective view of the landing field concerning 2nd Embodiment. It is a schematic diagram which shows the effect of the floor part of the landing field of 2nd Embodiment. It is a schematic cross section which shows the modification of a windbreak part.

An embodiment of a landing field according to the present invention will be described below with reference to the drawings.

(First embodiment)
FIG. 1 is a schematic perspective view of a landing field 11 according to the first embodiment. The landing field 11 is a landing field for a multi-copter 91 that flies with a plurality of horizontal rotors. The multicopter 91 is an unmanned rotary wing aircraft on which a pilot does not board, and flies by a control signal from an external transmitter or an autonomous flight function. The use of the multi-copter 91 is not particularly limited, and may be, for example, an airframe for aerial photography, a transport machine for cargo, or a hobby drone. The unmanned rotorcraft in the present invention also includes VTOL (Vertical Take-Off and Landing) aircraft.

The landing field 11 includes a fence portion 21 installed around the landing point 15 of the multicopter 91. The fence part 21 has a windbreak part 3 that blocks the inflow of wind to the landing point 15, and a ventilation part 4 through which the wind can pass easily than the windbreak part 3.

The fence part 21 of this embodiment is arranged in a substantially square shape in a plan view. The fence 21 has a side of about 4 m, and the landing point 15 surrounded by the fence 21 has an area of about 16 m ² . A part of the fence 21 is provided with an entrance/exit 19 for workers to enter and exit. The shape of the fence 21 and the landing point 15 in plan view is arbitrary. For example, the fence 21 may be arranged in a circular shape in plan view. Further, the fence portion 21 is not limited to the shape that completely surrounds the landing point 15, and may have a portion where the fence portion 21 is interrupted, for example, a portion of the doorway 19.

The landing field 11 of the present embodiment is for a small unmanned rotorcraft, but it is also possible to land a manned aircraft by providing a wider landing point 15. The landing site 11 can also be used as a takeoff and landing site for taking off and landing the multicopter 91.

The windbreak portion 3 is a wall portion having a vertical width of about 1.5 m, and protects the multicopter 91 during landing from crosswinds. The fence portion 21 has, on one side thereof, a see-through portion 31 in which the entire windbreak portion 3 is made of a light-transmitting acrylic plate. Thereby, the inside of the landing field 11 can be visually observed from the outside of the landing field 11, and the landing can be performed while confirming the state of the multicopter 91.

The windbreak part 3 may be any member as long as it can block the inflow of wind to the landing point 15, and its material, shape, and structure are not limited. As the material of the windbreak part 3, for example, resin, metal, wood, glass, rubber, cloth, or a combination thereof can be used. Further, the windbreak unit 3 is not limited to the one that can completely block the inflow of the wind to the landing point 15, and may have any shape and structure in which the wind does not easily pass as compared with the ventilation unit 4. The vertical width of the windbreak unit 3 may be any width that can block the crosswind, and can be appropriately changed according to the size of the aircraft to be landed and the required safety, but a sufficient protection effect from the crosswind is provided. In order to obtain the above, it is desirable that the width is 60 cm or more.

The ventilation part 4 is a mesh fence having a vertical width of about 70 cm. The ventilation section 4 is provided below the windbreak section 3. The ventilation unit 4 discharges the downwash of the multicopter 91 to the outside of the landing field 11 and suppresses the generation of vortex (vortex ring) around the rotor of the multicopter 91.

Since the ventilation part 4 of the present embodiment is composed of a mesh fence, animals and the like are prevented from entering the landing site 11 through the ventilation part 4. If there is no such concern, the ventilation part 4 may be simply a void. When the ventilation part 4 is made into a space and an operator takes in and out the multi-copter 91 from there, the entrance/exit 19 is not necessary. Further, the vertical width of the windbreak unit 3 can be appropriately changed as long as the downwash of the landing aircraft can be discharged to the outside of the landing field 11, but it is 15 cm to smoothly discharge the downwash. The above is desirable.

FIG. 2 is a schematic diagram for explaining the difference in the air flow around the rotor depending on the presence or absence of the ventilation part 4. As shown in FIG. 2(a), when the landing area is surrounded by a wall in order to suppress the influence of cross wind, in addition to the ground effect due to the downwash, the downwash generates an upward flow along the wall. Therefore, vortex (vortex ring) is likely to occur around the rotor of the multicopter. Vortex destabilizes the attitude control of the aircraft. If the vortex disrupts the plane of the aircraft immediately before landing, there is a risk of landing failure. Such a problem becomes more remarkable as the landing point 15 has a smaller area like the landing field 11. The helipad for manned helicopters must have the length of each side 1.2 times or more the length and width of the helicopter in the same direction, and usually an area of 20 m x 20 m or more is secured. The landing site 11 of the present embodiment is a landing site for unmanned aerial vehicles and is not required to have the same level of safety as a manned helicopter. Further, in order to obtain the windbreak effect without providing the windbreak unit 3 inefficiently and highly, it is desirable that the area thereof be 100 m ² or less.

As shown in FIG. 2B, the fence 21 of the landing field 11 is provided with the ventilation part 4, so that the downwash is discharged to the outside of the landing field 11. In the landing section 11, the windbreak section 3 of the fence section 21 prevents side winds, and the ventilation section 4 suppresses the generation of vortex around the rotor. It is possible to land safely. In particular, unmanned aerial vehicles have a smaller body weight than manned aerial vehicles and are more prone to crosswinds. According to the landing site 11 of the present embodiment, even such an unmanned aerial vehicle can safely land.

(Second embodiment)
FIG. 3 is a schematic perspective view of the landing field 12 according to the second embodiment. FIG. 4 is a schematic diagram showing the effect of the floor portion 5 of the landing field 12. Hereinafter, the configuration of the landing field 12 will be described with reference to FIGS. 3 and 4. In the following description, configurations having the same or similar functions as those of the previous embodiment will be denoted by the same reference numerals as those of the previous embodiment, and detailed description thereof will be omitted.

The landing field 12 is a landing field for a helicopter 92 flying with a main rotor that is a horizontal rotor. The helicopter 92 of this embodiment is also an unmanned rotary wing aircraft on which a pilot does not board, and flies by a control signal from an external transmitter or an autonomous flight function. The landing site 12 can also be used as a takeoff and landing site for taking off and landing the helicopter 92.

The landing field 12 includes a fence portion 22 installed around the landing point 15 of the helicopter 92. The fence part 22 has a windbreak part 3 that blocks the inflow of wind to the landing point 15, and a ventilation part 4 through which the wind can pass easily than the windbreak part 3. The uses and functions of the windbreak part 3 and the ventilation part 4 are the same as in the first embodiment. Moreover, the ventilation part 4 of this embodiment is a space|gap.

The landing field 12 of the present embodiment includes, in addition to the fence section 22, the floor section 5 installed at the landing point 15. The floor part 5 has a lattice-shaped floor surface having ventilation openings 51 through which wind can pass vertically. The lattice of the floor 5 is so fine that the skid of the helicopter 92 does not fit. As shown in FIG. 4, the floor 5 is supported by a plurality of columns 6 installed at the landing point 15. The ventilation section 4 of the fence section 22 is provided below the floor section 5.

In the landing field 12, the fence 22 includes the windbreak part 3 that blocks the inflow of wind to the landing point 15, and the floor 5 is formed with a ventilation port 51 through which the wind can pass vertically. The downwash passing through the ventilation port 51 is discharged from the ventilation unit 4 to the outside of the landing field 12. By landing the helicopter 92 higher than the surface of the ground, the landing field 12 of the present embodiment suppresses the influence of the ground effect at the time of landing of the helicopter 92 and enables the helicopter 92 to land more safely. There is.

In addition, the fence 22 of the present embodiment is also arranged in a substantially square shape in a plan view, and a part of the fence 22 is provided with an entrance/exit 19 for workers to enter and exit. The length of one side of the fence portion 22 and the vertical widths of the windbreak portion 3 and the air passage portion 4 are the same as those in the first embodiment.

The fence 22 has a window 32 on one side thereof, in which a part of the wall surface of the windbreak unit 3 is cut out. Thereby, the inside of the landing field 12 can be visually observed from the outside of the landing field 12, and the helicopter 92 can be landed while confirming the state of the helicopter 92.

(Variation of windbreak part)
FIG. 5: is a schematic cross section which shows the modification of the windbreak part 3 of the fence parts 21 and 22. As shown in FIG.

The windbreak unit 3 according to the present modification is provided with a rectifying unit 33 at the upper end of the windbreak unit 3 and in the vicinity thereof. A large number of mesh-shaped holes are provided on the wall surface of the flow regulating portion 33, so that the wind can pass through more easily than other portions of the windbreak portion 3.

When the cross wind is blocked by the windbreak unit 3, a turbulent flow is generated near the upper end of the windbreak unit 3 due to the difference in wind speed caused thereby. Turbulence may adversely affect the attitude control of the multicopter 91 and the helicopter 92. By providing the rectifying unit 33 at the upper end of the windbreak unit 3 and in the vicinity thereof, through which the wind can pass more easily than other portions of the windbreak unit 3, the difference in wind speed near the upper end of the windbreak unit 3 is reduced, and turbulence Becomes loose. In order to further enhance the rectifying action of the rectifying section 33, the mesh density may be gradually increased toward the upper end. The structure of the rectifying unit 33 is not limited to the mesh structure, and may be a lattice or a horizontal plate.

Although the embodiment of the present invention has been described above, the scope of the present invention is not limited to this, and various modifications can be made without departing from the spirit of the invention.

11, 12: Landing site, 15: Landing site, 19: Doorway, 21, 22: Fence part, 3: Windbreak part, 31: Transparent part, 32: Window part, 33: Rectification part, 4: Ventilation part, 5: Floor, 51: Vent, 6: Support, 91: Multicopter (unmanned rotorcraft), 92: Helicopter (unmanned rotorcraft)

Claims (6)

Equipped with fences installed around the landing points of rotorcraft,
The fence is
A windbreak that blocks the inflow of wind to the landing site;
A ventilation part through which the wind can pass easily than the windbreak part,
The ventilation section is provided below the windbreak section,
The windbreak part has a window part in which a part of the wall surface is cut out or a see-through part made of a light-transmitting material,
The landing field, wherein the rotorcraft is an unmanned rotorcraft that can be operated from outside the aircraft. Equipped with fences installed around the landing points of rotorcraft,
The fence is
A windbreak that blocks the inflow of wind to the landing site;
A ventilation part through which the wind can pass easily than the windbreak part,
The ventilation unit is provided below the windbreak portion,
A landing field, characterized in that a rectifying section is provided at an upper end of the windbreak section and in the vicinity thereof so that wind can pass through the windbreak section more easily than other portions of the windbreak section. The landing field according to claim 2, wherein the rectifying unit is a mesh, a lattice, or a horizontal plate with a gap gradually increasing toward the upper end. The vertical width of the windbreak part is 60 cm or more,
The landing field according to any one of claims 1 to 3, wherein a vertical width of the ventilation part is 15 cm or more. The landing field according to any one of claims 1 to 4, wherein the ventilation part is a mesh fence. The landing site according to any one of claims 1 to 5, wherein an area of the landing point surrounded by the fence portion is 100 m ² or less.

Images