DISC-SHAPED AVAILABLE VERTICAL TAKE-OFF AND LANDING AIRCRAFT

Abstract

A disc-shaped, vertically launching and landing aircraft, featuring the following: - an apron that widens towards the underside; - a disc-shaped rotor positioned on the underside of the apron and rotating relative to the apron; and - a plurality of blades arranged standing on an upper surface of the rotor and positioned radially from the center of the rotor, - wherein a cutout is formed in each of the majority of wings and - wherein, as the rotor rotates, the centrifugal force causes an airflow along the wing rotating with the rotor, wherein the airflow is swirled in a spiral by an airflow passing over the wing cutout in a direction substantially orthogonal to the wing, wherein the airflow flows along the wing in a radial direction of the rotor while swirling in the spiral, and wherein the airflow being expelled downwards through the skirt causes an upward movement.

Description

TECHNICAL AREA

[0001] The present invention relates to a disc-shaped aircraft capable of vertical take-off and landing. STATE OF THE ART

[0002] Various disc-shaped, vertical take-off and landing aircraft have been proposed as aircraft with a different flight principle than that of airplanes, helicopters, and the like (see, for example, patent literature JP 2008 - 137 527 A, JP 3 150 942 U and JP 2010 - 149 662 A). Such disc-shaped, vertical take-off and landing aircraft are configured so that their overall shape is disc-shaped, and vertical take-off and landing are achieved by expelling an airflow downwards.

[0003] These disc-shaped, vertically launching and landing aircraft are configured with a conical skirt and an air blower located in the center of the skirt. Air drawn in from above is blown horizontally through the air blower, flowing along an inner surface of the skirt and expelled downwards. The aircraft then ascends due to the force of the blown air.

[0004] DE 199 50 031 A1 describes a device by which a medium is accelerated by the centrifugal forces of a motor-driven rotor to generate axial thrust. The medium is drawn in by nozzles in the center of the rotor, which consists of a multitude of thin-walled, specially shaped channels, accelerated by centrifugal and tangential forces, and expelled axially through nozzles at the outlet. The outflowing and circulating medium, together with the profiled blade ring attached to the base body, generates additional axial thrust. In the "open ring nozzle rotor," the outer medium is used for thrust generation. In the "closed ring nozzle rotor," a special inner medium is used. The medium is guided to the nozzles by the guide ribs and drawn in by the nozzles.The resistance that must be overcome generates a counter-torque on the stationary base body, which corresponds to the motor torque. The ring-nozzle rotor can thus convert motor torque into axial thrust by means of the centrifugal force of a medium. BRIEF DESCRIPTION OF THE INVENTION Technical Problem

[0005] Conventional disc-shaped, vertical take-off and landing aircraft have a low lift force (the force required to ascend). Therefore, such aircraft are typically only suitable as toys and cannot be used as manned or unmanned aircraft with a high weight.

[0006] As a result of conducting intensive research relating to a disc-shaped, vertically launching and landing aircraft that can take off even if the aircraft has a high weight, such as a manned or unmanned aircraft, the inventor of the present invention was able to find a configuration in which a lift force can be achieved by which an aircraft with a high weight can take off.

[0007] The present invention is designed with regard to the foregoing points, and the object of the present invention is to provide a disc-shaped, vertically launching and landing aircraft that can ascend precisely even when it is heavy. Solution to the problem

[0008] The problem underlying the invention is solved by a disc-shaped, vertically taking-off and landing aircraft with the features of independent claim 1. Advantageous embodiments of the invention are specified in dependent claims 2 to 5. Advantageous effects of the invention

[0009] According to the present invention, the disc-shaped, vertically launching and landing aircraft is able to ascend precisely, even if the aircraft is heavy. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] The figures show: Fig. 1A a representation showing a configuration of a main area of ​​a disk-shaped, vertically launching and landing aircraft according to a present embodiment; Fig. 1B a representation showing a configuration that includes a cylindrical blower; Fig. 2A a top view of a Fig. 1B shown disc-shaped aircraft capable of vertical take-off and landing; Fig. 2B a cross-sectional view along a Fig. 2A shown line XX; Fig. 3 a perspective exploded view showing the in Fig. Figure 1B shows a disc-shaped, vertically launching and landing aircraft in a state in which it is disassembled into a cylindrical fan, skirt and rotor; Fig. 4A a representation showing an example of a configuration of a disk-shaped, vertically taking off and landing aircraft according to the present embodiment; Fig. 4B a representation showing a state in which the in Fig. Figure 4A shows a disc-shaped, vertically taking off and landing aircraft virtually cut across a surface that has a central axis; Fig. 5A a representation describing an airflow that flows in a spiral shape along a wing; Fig. 5B a representation describing an airflow swirling around a wing in a spiral shape; Fig. 6 a cross-sectional view showing a condition in which an airflow is generated on each blade on a rotor, which swirls around at high speed in a spiral shape and is expelled downwards through a skirt; Fig. 7A a top view of the disc-shaped, vertically taking off and landing aircraft, which has an opening and closing unit; Fig. 7B a cross-sectional view along a Fig. 7A shown line YY; Fig. 8A a cross-sectional view of the disc-shaped, vertically launching and landing aircraft, which has an oscillator; Fig. 8B a representation that describes an oscillation angle of the oscillator; Fig. 9 a representation showing an example of a guide configuration; Fig. 10A a cross-sectional view showing a state of the rotated and inclined guide; Fig. Figure 10B shows a cross-sectional view showing a condition in which the guide is rotated and tilted in a different direction. DESCRIPTION OF EXECUTION FORMS

[0011] In the following, embodiments of the disc-shaped, vertically taking off and landing aircraft according to the present invention are described with reference to the drawings.

[0012] Although the disc-shaped, vertically launching and landing aircraft described below is unmanned, the aircraft can also be configured to be manned.

[0013] Fig. Figure 1A is a representation showing a configuration of a main area of ​​a disk-shaped, vertically launching and landing aircraft according to the present embodiment, and Fig. Figure 1B is a representation showing a configuration that includes a cylindrical blower. Fig. 2A is a top view of the in Fig. 1B shown disc-shaped, vertically launching and loading aircraft, and Fig. 2B is a cross-sectional view along a [path / section] in Fig. Line XX shown in 2A.

[0014] Fig. Figure 3 is a perspective exploded view showing the contents. Fig. Figure 1B shows a disc-shaped, vertically taking-off and landing aircraft, disassembled into a cylindrical fan, a skirt, and a rotor. The illustration of the cylindrical fan blades is in Fig. 1B, Fig. 3 etc. omitted.

[0015] The disc-shaped, vertically launching and landing aircraft 1 according to the present embodiment has a skirt 2, a rotor 3 and a plurality of wings 4. As in Fig. As shown in Figure 1B etc., the aircraft may also have a cylindrical fan 5.

[0016] Apron 2 has an opening α (see Fig. 3) in the middle and has a circular shape that widens towards the underside. In Fig. 2B is the side of the apron 2 formed in a curved shape, but the apron 2 can also have a conical shape, for example.

[0017] A disc-shaped rotor 3 is positioned on the underside of the skirt 2. The rotor 3 is configured to rotate about a central axis A relative to the skirt 2. Depending on the configuration and material used in the disc-shaped, vertical take-off and landing aircraft 1, the rotor 3 rotates at a high speed of several tens of thousands of revolutions per minute.

[0018] The configuration for rotating rotor 3 is described later. When rotor 3 is arranged in the skirt 2, as shown in Fig. As shown in Figure 2B, an opening β (a space) is formed between the inner surface of the skirt 2 and the end area of ​​the rotor 3.

[0019] A plurality of blades 4 are arranged upright on the upper surface of the rotor 3. Each blade 4 is positioned radially from the center of the rotor 3.

[0020] According to the present embodiment, each blade 4 is arranged vertically to the rotor 3. Alternatively, each blade 4 can be arranged diagonally with respect to the rotor 3.

[0021] According to the present embodiment, a plate-shaped element 41, which has an opening γ (see Fig. 3) is provided in the middle area, attached to the upper ends of the wings 4. Each wing 4 is connected to the plate-shaped element 41.

[0022] When the rotor 3 is positioned in the skirt 2, the plate-shaped element 41 is inside the opening α (actually from the opening α (see Fig. 2B) positioned slightly downwards) in the middle area of ​​apron 2.

[0023] In a state where the rotor 3 is positioned in the skirt 2, that is, in a state where Fig. In the state shown in 1A, therefore, when, for example, air flows inwards from the opening γ in the central region of the plate-shaped element 41, the air flows between the vanes 4, that is, through the space formed by the skirt 2, the rotor 3 and the plate-shaped element 41, and through the areas separated by the vanes 4.

[0024] The air then flows in the radial direction of the rotor 3 along the wings 4, flows through the opening β and is expelled downwards from the skirt 2.

[0025] As described above, in the disc-shaped, vertically launching and landing aircraft 1 according to the present embodiment, an inner space is formed which is surrounded by the skirt 2, the rotor 3 etc., as well as an air path which is separated by the wings 4.

[0026] When the rotor 3 rotates relative to the skirt 2 as described above, the centrifugal force generates an airflow along the wing 4, which rotates with the rotor 3.

[0027] To generate such an airflow, outside air is drawn in through the opening γ of the central area of ​​the plate-shaped element 41, and the airflow passes through the respective path separated by the blades 4. The airflow is then expelled downwards from the opening β between the skirt 2 and the rotor 3.

[0028] Sections 4a, which are formed in each wing 4, and the vortex in a spiral shape that arises in the airflow, will be described later.

[0029] According to the present embodiment, as described below, air flows in the region of opening γ in the central area of ​​the plate-shaped element 41 along the wing 4 and is expelled from opening β between the skirt 2 and the rotor 3. Therefore, a low pressure is created in the region of opening γ in the central area of ​​the plate-shaped element 41, that is, in the central area of ​​the rotor 3.

[0030] According to the present embodiment, as in Fig. As shown in Figure 1B, a cylindrical fan 5 is arranged above the central area of ​​the rotor 3. The cylindrical fan 5 rotates and sends air to the central area of ​​the rotor 3.

[0031] Similar to the rotor 3, the cylindrical blower 5 is configured to rotate around the central axis A in relation to the skirt 2.

[0032] According to the present embodiment, the cylindrical fan 5 rotates on the same axis (that is, around the central axis A) in the same direction and at the same speed as the rotor 3. The foregoing example is described below; however, the cylindrical fan 5 and the rotor 3 need not have the same axis of rotation, the same direction of rotation, or the same speed of rotation. The configuration for rotating the cylindrical fan 5 is described later.

[0033] On an inner surface of a cylindrical area of ​​the cylindrical blower 5, a plurality of blower blades 51 are arranged such that they protrude inwards in a substantially horizontal direction.

[0034] Each blower blade 51 has a blade cross-section and is arranged such that the blade surface is inclined with respect to a horizontal surface.

[0035] As the cylindrical blower rotates, air is drawn in above the cylindrical blower 5 and forced downwards. The airflow expelled from the cylinder is dispersed in all directions by the cylinder's rotation, and the air is directed towards the vane 4.

[0036] Here, an example of the configuration of the disc-shaped, vertically launching and landing aircraft 1 according to the present embodiment is described.

[0037] Fig. Figure 4A is a representation showing an example of a configuration of a disk-shaped, vertically launching and landing aircraft according to the present embodiment. Fig. 4B is a representation that shows a state in which the in Fig. 4A shows a virtually cut-off section of a disc-shaped, vertically launching and landing aircraft on a surface which has the central axis A.

[0038] According to the example for the configuration of the disc-shaped, vertically launching and landing aircraft 1, a cylindrical upper support 6 with legs 61 is attached to the skirt 2 or is formed in one piece with the skirt 2, and the upper support 6 is positioned on the upper side of the middle area of ​​the skirt 2.

[0039] The cylindrical blower 5 is positioned on the inside of the cylinder area of ​​the upper stand 6 with a bearing 7 in between.

[0040] The cylindrical blower 5 can rotate around the central axis A with the bearing 7 and is held in such a way that it does not move in a vertical direction with respect to the upper stand 6.

[0041] The cylindrical blower 5 rotates around the central axis A by means of a drive mechanism, such as a motor (not shown), arranged in the upper stand 6.

[0042] A downwardly projecting shaft 31 is arranged in the central region of the rotor 3, which is equipped with the blades 4. The shaft 31 is held by a lower support 8, which is attached to the lower surface of the skirt 2 with a bearing 9 between it and the skirt. The lower support 8 is formed with a narrow square bar or the like, such that the discharge of the airflow from the opening β between the skirt 2 and the rotor 3, as described above, is not obstructed.

[0043] In the lower edge region of the shaft 31 in the lower stator 8 a drive mechanism is arranged, such as a motor (not shown), and the rotor 3 rotates around the central axis A by rotating the shaft 31 with the drive mechanism.

[0044] Next, the cutout in each wing 4 and the ascent principle of the disc-shaped, vertically launching and landing aircraft 1 according to the present embodiment will be described.

[0045] According to the present embodiment, as shown in the drawings, for example in Fig. In Figure 1A, a cutout 4a is formed at the upper edge of the outer side, as viewed from the central axis A, in each of the plurality of blades 4 arranged upright on the upper surface of the rotor 3. Each drawing shows an example where the cutout 4a is rectangular (that is, a rectangular cutout formed in the rectangular blade 4); however, the cutout 4a need not be rectangular. The blade 4 need not be rectangular either.

[0046] The ascent principle of the disc-shaped, vertically launching and landing aircraft 1 according to the present embodiment is described below.

[0047] When rotor 3 rotates at high speed in a direction that is in Fig. As shown in 5A with an arrow R, the air in the central area of ​​the rotor 3 flows along the wing 4 due to centrifugal force, as in Fig. 5A and Fig. 5B shown. As in Fig. 5A and Fig. As shown in 5B, an airflow F is therefore generated along the wing 4, which rotates with the rotor 3 (see F1 in the drawing).

[0048] Due to the high-speed rotation of the rotor 3, the air flows on the leading edge of the wing 4 in the direction of rotation over the cutout 4a of the wing 4 and flows in a substantially orthogonal direction to the wing 4. Then an airflow f is generated that flows towards the trailing edge of the wing 4 in the direction of rotation.

[0049] Then, due to the difference in velocity compared to the low-velocity area behind the cutout 4a, the airflow f passing over the opening 4a is swirled around. Therefore, the airflow F flowing along the wing 4 swirls around, and the airflow F flows along the wing 4 while swirling in a spiral shape (see F2 in the drawings).

[0050] The reason why the airflow F in the drawing in Fig. The reason 5A appears to be bent to the left is that, due to the rotation of the rotor 3, the wing 4 moves to the left in the drawing, while the airflow F flows along the wing 4. Therefore, the airflow F is shown moving to the left in the drawing, and this does not mean that the airflow F is flowing away from the wing 4.

[0051] Then the airflow F flows along the wing 4 as it swirls around in a spiral, and even after separation from the wing 4, the rotational speed of the vortex increases during the flow in the radial direction of the rotor 3 due to friction with the rotating rotor 3 and the stationary skirt 2 (see F3 in the drawings).

[0052] The airflow F then flows in the radial direction of the rotor 3 as it swirls around at high speed in a spiral; the direction of the airflow F in which it moves forward is changed downwards by the skirt 2, and the airflow F is expelled downwards from the opening β between the skirt 2 and the rotor 3 (see F4 in the drawings).

[0053] Then the airflow F, which swirls around at high speed in a spiral, is generated by all of the blades 4 formed in the rotor 3, and the airflow F is, as in Fig. 6 shown, pushed downwards through apron 2.

[0054] Then the disc-shaped, vertically launching and landing aircraft 1 rises due to a reaction to the downwardly expelled airflow F.

[0055] The foregoing describes the ascent principle of the disc-shaped, vertically launching and landing aircraft 1 according to the present embodiment.

[0056] If the cutout 4a in the wing 4 is not formed, the air in the central region of the rotor 3 flows along the wing 4 due to centrifugal force as the rotor 3 rotates, according to the disc-shaped, vertically taking off and landing aircraft 1, creating the airflow F (F1). However, the flow is dispersed as it moves forward in the radial direction of the rotor 3 and its speed decreases.

[0057] Even after the airflow F is expelled downwards, the expelled airflow is dispersed, and the speed of the expelled airflow decreases drastically; therefore, no large buoyant force (no large force to rise) can be achieved.

[0058] By arranging a cutout 4a in the wing as in the disc-shaped, vertically launching and landing aircraft 1 according to the present invention, the airflow F flowing along the wing 4 swirls around it, and the airflow F flows in the radial direction of the rotor 3 along the wing 4 while swirling around in a spiral shape.

[0059] Even though the airflow F flows in the radial direction of the rotor 3, the airflow F is therefore not dispersed. Consequently, the kinetic energy of the airflow F is maintained in the radial direction, and a reduction in the velocity of the flow is prevented.

[0060] When the airflow F is expelled downwards through the skirt 2 from the opening β between the skirt 2 and the rotor 3, the spiraling state is maintained. Therefore, the airflow F is not dispersed, and the kinetic energy of the airflow F in the expulsion direction is kept at a high value even after expulsion.

[0061] Since the airflow F is forcefully expelled downwards, the disc-shaped, vertically launching and landing aircraft 1 according to the present embodiment is therefore able to achieve a very large lift force.

[0062] Since an extremely large lift force (an extremely large force for ascending) can be achieved in the disc-shaped, vertically launching and landing aircraft 1 according to the present embodiment as described above, the disc-shaped, vertically launching and landing aircraft 1 can ascend to a sufficient degree even if the disc-shaped, vertically launching and landing aircraft 1 is heavy.

[0063] According to the disc-shaped, vertically launching and landing aircraft 1 of the present embodiment, the aircraft can therefore reliably take off, even if the disc-shaped, vertically launching and landing aircraft 1 is heavy, such as in the case of a manned or unmanned aircraft.

[0064] According to the present embodiment, the air in the central region of the rotor 3 flows as an airflow F due to centrifugal force, as described above. Therefore, a negative pressure is created in the central region of the rotor 3 (that is, the region of the opening γ in the center of the plate-shaped element 41). Since the rotor 3 rotates at a high speed, a high negative pressure is generated in the central region of the rotor 3.

[0065] According to the present embodiment, the airflow F flowing along the wing 4 swirls around in a spiral shape, as described above, and a low pressure is created in the center of the vortex. Therefore, the low pressure is further increased in the central region of the rotor 3.

[0066] If the degree of negative pressure in the central area of ​​rotor 3 is increased, the air in this area cools rapidly, and water vapor condenses in the air. Due to the condensation of the water vapor, the volume of air in this area decreases rapidly.

[0067] Since a very high negative pressure is created in the central area of ​​the rotor 3, a large amount of air that is present above it is drawn in through the opening γ in the middle of the plate-shaped element 41.

[0068] As described above, the disc-shaped, vertically launching and landing aircraft 1 according to the present embodiment draws in a large quantity of air from above and is also able to forcefully expel the spiraling airflow F downwards.

[0069] Therefore, it is possible to achieve a very large lift force (a very large force for ascending) in the disc-shaped, vertically launching and landing aircraft 1 according to the present embodiment.

[0070] If the cylindrical blower 5 described above, as in Fig. As shown in 1B, the air above the central area of ​​the rotor 3 (that is, above the opening γ in the middle of the plate-shaped element 41) can be efficiently directed to the wing 4 by the rotation of the cylindrical fan 5.

[0071] Since an airflow directed through the cylindrical fan 5 is added to the airflow F generated by the centrifugal force due to the rotation of the rotor 3, the flow velocity of the airflow F flowing radially along the wing 4 is increased, and the flow velocity of the expelled (outflowing) airflow F increases even further. Consequently, it is possible to continuously increase the lift force (the force causing ascent) of the disc-shaped, vertically launching and landing aircraft 1.

[0072] As described above, a low pressure is created in the central region of the rotor 3 in the disc-shaped, vertically launching and landing aircraft 1 according to the present embodiment, and the air in this region is cooled. However, if the thermal conductivity of the material used in the rotor 3 and the wing 4 is low, the rotor 3 and the wing 4 will not be cooled, even if the air in the central region of the rotor 3 is cooled. Consequently, the air passing through the rotor 3 and the wing 4 is heated, and this can impair the cooling of the air in this region.

[0073] If the rotor 3 and the wing 4 are made of a material with high thermal conductivity, such as a metal, the air in the central area of ​​the rotor 3 is easily cooled, and this is preferred.

[0074] If the rotor 3 and the wing 4 are made of a high-density material, a high inertial force can be obtained when the rotor 3 rotates at a high speed.

[0075] Therefore, even if the orientation of the disc-shaped, vertically launching and landing aircraft 1 suddenly changes, for example due to a gust of wind, the rotation of the rotor 3 can be maintained at a high speed without being affected by the change in orientation. Movement in a horizontal direction

[0076] The preceding embodiments describe the ascent of the disc-shaped, vertically launching and landing aircraft 1. Alternatively, it is possible to reduce the rotational speed of the rotor 3 and the flow velocity of the expelled (outflowing) airstream F. This makes it possible to reduce the altitude of the disc-shaped, vertically launching and landing aircraft 1 and to land the aircraft.

[0077] According to the configuration described below, it is possible to move the disc-shaped, vertically launching and landing aircraft 1 in a horizontal direction (that is, to move it forward, move it backward, or move it sideways).

[0078] This means that an opening and closing unit, capable of opening and closing, is formed in a region of the lower edge of the skirt 2. By opening the opening and closing unit, the airflow F, which flows in the radial direction of the rotor 3 along the wing 4, as described above, can be expelled in a straight line without altering the direction in which it travels forward through the skirt 2. As a result, a forward propulsive force in the horizontal direction (i.e., for forward motion) can be achieved without tilting the nose of the disc-shaped, vertically launching and landing aircraft 1.

[0079] The details are described below.

[0080] Fig. Figure 7A is a top view of the disc-shaped, vertically taking off and landing aircraft, which has an opening and closing unit. Fig. 7B is a cross-sectional view along a [path / section] in Fig. Line YY shown in Figure 7A. The following description describes a case in which the disc-shaped, vertically launching and landing aircraft 1 has the cylindrical fan 5, but the same applies to the configuration that does not have the cylindrical fan 5.

[0081] As in Fig. As shown in Figure 7A, a region of the lower end of the skirt 2 in the disc-shaped, vertically launching and landing aircraft 1 is cut and separated to form an opening and closing unit 21, and the opening and closing unit 21 is attached to the cut-out region by a hinge 22. Thus, in this case, an opening and closing unit 21, which can open and close in a vertical direction, can be formed in the region at the lower end of the skirt 2.

[0082] The opening and closing unit 21 can, for example, be configured to open and close in one direction, to the left and right (a horizontal direction). Instead of the configuration for opening and closing by means of a hinge 22, it is possible, for example, to configure the opening and closing unit 21 to open and close by sliding along the skirt 2. The method for opening and closing the opening and closing unit 21 is not limited to a specific procedure.

[0083] If the opening and closing unit 21, which can open and close an area of ​​the lower end of the apron 2, is configured, then when the opening and closing unit 21 is open, as shown in Fig. Figure 7B shows the airflow F flowing in the radial direction of the rotor 3 along the wing 4 in the area where the opening and firing unit 21 is open, being expelled straight through the skirt 2 without changing the direction in which it is moving forward.

[0084] In response to the above, the disc-shaped, vertically launching and landing aircraft 1 is therefore able to move in the horizontal direction (in this case, to the left in the drawing) without tilting its nose. In the area of ​​the skirt 2, with the exception of the opening and closing unit 21, the airflow F is expelled downwards, as described above (the airflow F flows downwards). Therefore, the disc-shaped, vertically launching and landing aircraft 1 can move in a hovering state in the horizontal direction.

[0085] Taking into account that the disc-shaped, vertically launching and landing aircraft 1, which is moving in the direction to the left in the drawing, is moving forward, the disc-shaped, vertically launching and landing aircraft 1, if the opening and closing unit 21 in the disc-shaped, vertically launching and landing aircraft 1 is designed analogously to the above on the left side of the illustration (that is, on the front side of the disc-shaped, vertically launching and landing aircraft 1), is able to move backward, although the corresponding illustration has been omitted.

[0086] If the opening and firing unit 21 is formed on the upper and lower sides of the disc-shaped, vertically launching and landing aircraft 1 as shown in the illustration (i.e., on the starboard and port sides of the disc-shaped, vertically launching and landing aircraft 1), the disc-shaped, vertically launching and landing aircraft 1 can move sideways.

[0087] As described above, the disc-shaped, vertically launching and landing aircraft 1 can be moved by forming an opening and closing unit 21, which can open and close, in a region of the lower end of the skirt 2 and by opening the opening and closing unit 21 in the direction opposite to the side on which the opening and closing unit 21 is formed.

[0088] In this case, an opening and closing mechanism, not shown, is arranged in the disc-shaped, vertically launching and landing aircraft 1 to open and close the opening and closing unit 21. Considering the control of an orientation, roll control, and pitch control.

[0089] According to the configuration below, roll control and pitch control can be performed to control the orientation of the disc-shaped, vertically launching and landing aircraft 1.

[0090] This means that at multiple points on the lower end of the skirt 2, an oscillator is configured to oscillate towards the inside of the skirt 2, and an oscillation angle is specified for each oscillator such that they differ from one another. This allows a different lift force to be generated in each area of ​​the disc-shaped, vertically launching and landing aircraft where an oscillator is configured. Consequently, roll control and pitch control can be implemented in the disc-shaped, vertically launching and landing aircraft 1. The details are described below.

[0091] Fig. Figure 8A is a cross-sectional view of the disc-shaped, vertically launching and landing aircraft, which features an oscillator, and Fig. Figure 8B is a diagram describing the oscillation angle of the oscillator. The following describes an example where the disc-shaped, vertically launching and landing aircraft 1 has the cylindrical fan 5; however, the same applies to the configuration where the cylindrical fan 5 is not fitted.

[0092] Similar to the one in Fig. In the opening and closing unit 21 shown in Figure 7A, for example, an oscillator 23 is created by cutting out a plurality of positions at the lower end of the skirt 2 in the disc-shaped, vertically launching and landing aircraft 1, for example, at the lower end of the skirt 2 on the port side and the starboard side of the disc-shaped, vertically launching and landing aircraft 1. The oscillator 23 is attached to the cut-out area by a joint 24. Thus, the oscillator 23, which can swing towards the inside of the skirt 2, can be formed at a plurality of positions at the lower end of the skirt 2.

[0093] In this case, an opening and closing mechanism, not shown, is arranged in the disc-shaped, vertically launching and landing aircraft 1 to open and close the opening and firing unit 21. The opening and closing unit 21 described above can be configured to also function as the oscillator 23.

[0094] If an oscillator 23, which can oscillate, is formed at a plurality of positions at the lower end of the skirt 2, as in Fig. As shown in Figure 8A, the direction of the airflow F can be changed by the oscillation angles θ1 and θ2 of the oscillator 23 when the direction of the airflow F, which flows in the radial direction of the rotor 3 along the wing 4, is changed downwards by the oscillator 23 of the skirt 2.

[0095] That is, if the oscillation angle θ1 is as in the one in Fig. Since the oscillator 23 shown in Figure 8A is relatively small on the port side, the airflow F flowing along the wing 4 is expelled downwards through the oscillator 23. If the oscillation angle θ2 is as in the one shown in Figure 8A, the airflow F is expelled downwards. Fig. When the oscillator 23 shown in 8A is large on the starboard side, the airflow F flowing along the wing 4 is expelled through the oscillator 23 towards the inner side.

[0096] As in Fig. As shown in Figure 8B, the oscillation angle θ of the oscillator 23 is defined as an angle formed by a tangent line of the oscillator 23 at the joint 24 before an oscillation of the oscillator and a tangent line of the oscillator 23 at the joint 24 after an oscillation of the oscillator 23.

[0097] In contrast to the case where the airflow F is expelled downwards on the port side, as in oscillator 23, the buoyant force on the starboard side becomes low when the airflow F is expelled towards the inner side on the starboard side, as in oscillator 23.

[0098] As described above, for example, by providing the oscillator 23 on the port and starboard sides of the disc-shaped, vertically launching and landing aircraft 1 and by specifying the oscillation angles θ1 and θ2 such that they differ, a different lift force can be generated in each area of ​​the disc-shaped, vertically launching and landing aircraft 1 in which the oscillators 23 are formed, that is, in this case on the port and starboard sides of the disc-shaped, vertically launching and landing aircraft 1.

[0099] By oscillating the oscillators 23 with oscillation angles θ1 and θ2, which differ from each other on the port and starboard sides of the disc-shaped, vertically launching and landing aircraft 1, as in Fig. As shown in 8A, the buoyant force is determined by the in Fig. In the example shown in Figure 8A, the pressure on the port side of the disc-shaped, vertically launching and landing aircraft 1 is therefore greater than on the starboard side. Therefore, in this case, it is possible, as shown in the drawings with an arrow r, to roll the disc-shaped, vertically launching and landing aircraft 1 so that the port side rises and the starboard side sinks.

[0100] Although the illustration is omitted, the disc-shaped, vertically launching and landing aircraft 1 can be controlled, if the oscillation angles θ1 and θ2 of the oscillators 23 on the port and starboard sides of the disc-shaped, vertically launching and landing aircraft 1 are reversed, so that it rolls in the opposite direction, causing the starboard side to rise and the port side to sink (the foregoing is roll control).

[0101] Fig. 8A describes the left side of the drawing as being the port side of the disc-shaped, vertically taking off and landing aircraft 1, and the right side of the drawing as being the starboard side of the disc-shaped, vertically taking off and landing aircraft 1. Alternatively, the left side of Fig. 8A, for example, is considered the front end of the disc-shaped, vertically taking off and landing aircraft 1, and the right side of Fig. 8A is considered to be the rear end of the disc-shaped, vertically launching and landing aircraft 1.

[0102] If an oscillator 23 is formed at the front end and at the rear end of the disc-shaped, vertically launching and landing aircraft 1, and control is carried out such that the oscillation angles θ of the oscillators 23 differ from each other, it is possible to control the disc-shaped, vertically launching and landing aircraft 1 so that it pitches, causing the front end to rise and the rear end to descend, or causing the rear end to rise and the front end to descend (the foregoing is called pitch control).

[0103] According to the above configuration, the opening and closing unit 21 and the oscillator 23 are configured at the forward and aft ends, as well as on the port and starboard sides, of the disc-shaped, vertically launching and landing aircraft 1. Alternatively, the above units may be configured in other positions, and the positions and number of units of the opening and closing unit 21 and the oscillator 23 that are configured shall be determined in a suitable manner. Yaw control

[0104] According to the configuration described below, yaw control can be implemented as a way to control the orientation of the disc-shaped, vertically launching and landing aircraft 1.

[0105] This means that a guide can be arranged on the inner surface of the skirt 2 to change the discharge direction of the airflow F such that the direction and magnitude of the force for rotating the skirt 2 about its central axis A (that is, about the central axis A of the disc-shaped, vertically launching and landing aircraft 1) are changed. An example is described below in which the disc-shaped, vertically launching and landing aircraft 1 has the cylindrical fan 5; however, the same applies to the configuration that does not have the cylindrical fan 5.

[0106] For example, in Fig. As shown in Figure 9, a guide 25, essentially in the form of a plate, extends from the inner surface 2a of the skirt 2 in an inward direction. The guide 25 can rotate about a pivot axis 25a.

[0107] Such guides 25 are arranged everywhere around the entire circumference of the skirt 2, or one or more guides 25 are arranged at suitable positions on the skirt 2. A rotary mechanism (not shown) is arranged in the disc-shaped, vertically launching and landing aircraft 1 to rotate the guide 25.

[0108] If the guide 25 is then rotated, for example, and, as shown in the cross-sectional view in Fig. As shown in Figure 10A, the direction of the expelled airflow F on the far side of the illustration is inclined from the top right to the bottom left.

[0109] Since in this case a force in the direction to the right is added to the guide 25 on the far side in the illustration by the airflow F, a force is therefore exerted from the top side downwards when considering the disc-shaped, vertically taking off and landing aircraft 1, such that the skirt 2 rotates in a clockwise direction around the central axis A.

[0110] If the guide 25 is alternatively rotated, for example, and as shown in the cross-sectional view in Fig. As shown in Figure 10B, the direction of the discharge of the airflow F can be changed so that the direction of the discharged airflow F on the distant side of the illustration is a flow direction from the top left of the illustration to the bottom right of the illustration.

[0111] Since, in this case, the airflow F adds a force in the left direction to the guide 25 on the far side of the diagram, the force, when considering the disc-shaped aircraft 1 taking off and landing vertically, is exerted downwards from the top such that the skirt 2 rotates counterclockwise around the central axis A. The direction of the force rotating the skirt 2 around the central axis A can be changed by altering the inclination of the guide 25.

[0112] Then it can be ensured that the force for rotating the apron 2 around the central axis A in both examples, which is in Fig. 10A and Fig. As shown in 10B, the size increases by increasing the inclination of the guide 25 with respect to the central axis A.

[0113] Therefore, by changing the inclination of the guide 25 with respect to the central axis A and changing the direction of the airflow F, it is possible to change the magnitude of the force required to rotate the skirt 2 around the central axis A.

[0114] As described above, it is possible to precisely change the direction and magnitude of the force for rotating the skirt 2 about the central axis A by arranging the guide 25 described above on the inner surface of the skirt 2 of the disc-shaped, vertically launching and landing aircraft 1 and by changing the discharge direction of the airflow F by changing the inclination of the guide 25 with respect to the central axis A.

[0115] By rotating the skirt 2 around the central axis A, the disc-shaped, vertically launching and landing aircraft 1 can then be rotated clockwise or counterclockwise around the central axis A when viewed from the top side, and it is possible to precisely perform yaw control of the disc-shaped, vertically launching and landing aircraft 1.

[0116] If the inclination of the guide 25 with respect to the central axis A becomes too large, the force to rotate the skirt 2 around the central axis A becomes small, and the guide 25 impairs the expulsion of the airflow F.

[0117] Therefore, the rotation of the guide 25 around the axis of rotation 25a (that is, the changing of the inclination of the guide 25 with respect to the central axis A) is carried out within a suitable range so as not to impair the expulsion of the airflow F.

[0118] The disc-shaped, vertically launching and landing aircraft 1 according to the present embodiment is configured such that the rotor 3 rotates about the central axis A with respect to the skirt 2. When the cylindrical fan 5 is arranged, the cylindrical fan 5 also rotates about the central axis A.

[0119] If no action is taken (that is, if the guide 25 is held in a direction pointing straight downwards), the skirt 2 therefore receives a counterforce from the rotor 3 and the cylindrical blower 5, and the skirt 2 rotates around the central axis A in a direction opposite to that of the rotor 3.

[0120] According to the present embodiment, the guide 25 therefore rotates about the axis of rotation 25a, which is inclined such that the force to rotate the skirt 2 about the central axis A is generated in the skirt 2 in a direction opposite to that of the rotor 3 etc. (that is, a counter-torque with respect to the rotation of the rotor 3 etc.).

[0121] By generating the counter-torque as described above, the skirt 2 does not rotate around the central axis A and remains stationary when the disc-shaped, vertically launching and landing aircraft 1 does not perform the yaw movement.

[0122] The present invention is not limited to the foregoing embodiments and can be modified in a suitable manner without departing from the scope of the present invention. Industrial applicability

[0123] The present invention can be applied to aircraft that take off and land vertically. REFERENCE MARK LIST 1 disc-shaped, vertically taking off and landing aircraft 2 aprons 2a inner surface of the apron 3 Rotor 4 wings 4a Excerpt 5 cylindrical blower 21 Opening and closing unit 23 Oscillator 25 Leadership 51 blower blades A central axis F Airflow f airflow θ angle of oscillation

Claims

[1] A disc-shaped, vertically launching and landing aircraft, comprising the following features: - an apron that widens towards the underside; - a disc-shaped rotor positioned on the underside of the apron and rotating relative to the apron; and - a plurality of blades arranged standing on an upper surface of the rotor and positioned radially from the center of the rotor, - wherein a cutout is formed in each of the majority of wings and - wherein, as the rotor rotates, the centrifugal force causes an airflow along the wing rotating with the rotor, wherein the airflow is swirled in a spiral by an airflow passing over the wing cutout in a direction substantially orthogonal to the wing, wherein the airflow flows along the wing in a radial direction of the rotor while swirling in the spiral, and wherein the airflow being expelled downwards through the skirt causes an upward movement. [2] Disc-shaped, vertically taking off and landing aircraft according to claim 1, - wherein a cylindrical blower is positioned above the rotor, the cylindrical blower having blower blades that rotate and send air to a central area of ​​the rotor. [3] Disc-shaped, vertically taking off and landing aircraft according to claim 1 or 2, - wherein an opening and closing unit that can open and close is formed in an area of ​​a lower end of the apron and - wherein, when the opening and closing unit opens, the airflow, which flows in a radial direction of the rotor along the wing, is expelled in a straight line without any change in direction by the skirt. [4] Disc-shaped, vertically taking off and landing aircraft according to any one of claims 1 to 3, - wherein oscillators are formed at a plurality of positions at a lower end of the apron, each of the oscillators being able to oscillate towards an inside of the apron, and - wherein the oscillation angles of the oscillators are specified such that they differ from each other and that a different lift force can be generated in each area of ​​the disc-shaped, vertically launching and landing aircraft in which the oscillators are designed. [5] A disc-shaped, vertically launching and landing aircraft according to any one of claims 1 to 4, further comprising a guide on an inner surface of the skirt, wherein the guide changes the direction of the airflow and changes the direction and / or magnitude of a force by which the skirt is rotated about a central axis of the skirt.

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