JP3793545B1 - A rotor blade with a shroud with a bottom plate that enables storage and exhibition and an aircraft with it attached - Google Patents

Abstract

An object of the present invention is to make it possible to store a rotor blade with a shroud in a bottom plate, and when the aircraft descends to the ground and stops the rotor blade with a shroud, the occupation of the space can be minimized. If it is an exhibition book, it will be a problem to make it an aircraft that can fly and have a propulsive force .
In the present invention, the rotor blade with shroud can be stored in the bottom plate to reduce the occupied area of the airframe when parked on the ground, and when the surface is pulled out from the bottom plate and expanded, the rotating surface of the rotor blade with shroud is displayed. Can easily stand upright with respect to the fuselage and can generate lift and propulsion to facilitate the operation of an aircraft with shroud-equipped rotors attached to the fuselage.
[Selection] Figure 23

Description

The present invention relates to a rotor blade with a shroud with a bottom plate that enables storage and exhibition books, and a rotor blade with a shroud with a bottom plate that enables storage and exhibition books, in a forward direction during cruise of an aircraft. It is related with the implementation | achievement method of the aircraft which can fly freely in the air with the rotor blade with a shroud attached to the side surface and the side wall of the airframe in the case of the standard .

The history of the helicopter is at odds with the beginning, but it was made in 1923 in Barcelona, Spain , with the hinges currently in use, enabling cyclic control and collective pitch control in 1924 About 80 years have passed since it was invented with the coaxial reversing helicopter No. 3 of Pescara (Marquis Raul Pateras Pescara) , which flew about 10 minutes in January of the year . During this time, there are aircraft that tried to generate force at the wing tip by ejecting gas from the wing tip, attaching a ramjet to the wing tip, or attaching a turbo jet itself, but many of them are driven I have been flying by connecting the power for the rotating shaft of the rotor blade core. For this reason, hereinafter, the type in which power is connected to the rotating shaft of the blade core and the lift generated by the rotating blade is transmitted to the airframe via the rotating shaft is referred to as a conventional helicopter.

The method of connecting the power for driving the rotating blades to the rotating shaft of the blade core portion is less efficient in generating torque due to the principle of leverage than the method of generating the power at the blade tips of the rotating blades. For this reason, injecting gas from the tip of a blade, attaching a turbojet to the tip of a rotor blade having a diameter of 60 m (rotation radius of 30 m), rotating in the UK, a concept of attaching a ramjet, In this way, there is an attempt in which an electromagnet and a permanent magnet are arranged between a blade tip and a shroud covering the blade to form a driving principle of a linear motor, and the driving force at the blade tip having the highest efficiency is pursued. However, in an attempt to obtain the force action point at the blade tip, the number of action points is limited by the number of rotor blades. For example, two blades have two blades, five blades have five blades, and eight blades have eight blades. Just need to generate the force to get full lift. For this reason, a turbojet, a ramjet, or a set of electromagnets and permanent magnets requires generation of a remarkably large force, so that the required force cannot be obtained and cannot be realized.

A conventional helicopter that connects power to the rotating shaft of the rotor blade core is an open blade tip that floats the blade tip of the rotating blade in the air, and the lift generated by the rotating blade passes through the rotating shaft. Is transmitted to. In this case, if the blade width of the rotor blade is the same and the angle of the rotor blade with respect to the rotating surface (hereinafter referred to as the pitch angle) is constant from the blade tip to the blade center, the tip of the rotor blade and the blade core Since the relative speed with respect to the atmosphere (hereinafter referred to as air speed) is different in the part, the generated lift is remarkably large at the tip of the blade having a high air speed and extremely small at the blade center having a low air speed. Therefore, when the lift at the blade tip of the conventional helicopter is significantly different from that at the blade center, the blades of the rotor blade may be bent and the lift may be reduced or lost. For this reason, in a conventional helicopter, the blade width of the blade tip of the rotor blade is narrowed or the pitch angle is laid close to 0 ° as much as possible (the blade tip becomes minus −2 ° or −3 °). (There is also a pitch angle), and the lift generated at the blade center is suppressed, or conversely, the blade width of the blade core is increased and the pitch angle is increased to about 15 ° to increase the lift generated at the blade center. As shown by 49, the ideal form is to generate uniform lift throughout the rotor blades.

Therefore, in order for the rotor blades to generate the lift generated most efficiently, the rotor blade angle relative to the relative wind (hereinafter referred to as the angle of attack) is said to be 10 to 7 °. In the helicopter rotor blade, the part where the pitch angle that is the angle of attack is 10 to 7 ° is a part of the rotor blade as shown in FIG. Since it is not possible to apply a pitch angle of 10 to 7 ° to a blade tip that can generate lift, it has a structure that makes it impossible to generate lift efficiently. Become.

When obtaining the point of action of the force at the most efficient blade tip from the lever principle, Patent Document 2 and Patent Document 4 describe a method in which the blade tip of a rotating blade is used as a rotating duct as a method not limited by the number of rotating blades. We proposed a method of rotating by applying the linear motor driving principle around the outer circumference of the rotating duct or the outer ring of the rotating ring that is connected by a ring or ring. As a result, the arrangement of electromagnets and permanent magnets, which constitute the driving principle of the linear motor, is removed from the limitation of the number of blades and becomes the entire circumference of the rotor blade, making it possible to have many action points of driving force. . By setting the point of action to the entire circumference, the magnitude of the force that should be generated by one set of the electromagnet and the permanent magnet constituting the linear motor is that the set of the electromagnet and the permanent magnet is generated at the blade tip so far. Compared to the magnitude of power, it can be dramatically reduced. As a result, the sizes of the electromagnet and the permanent magnet, the amount of current to be passed, and the selectivity of the thickness of the electric wire are increased, and the calculation becomes easy and can be realized.

However, the ducted fan using electromagnetic force disclosed in Patent Document 4 has a mechanism corresponding to large expansion and contraction of the blades of the rotating blades, assuming that the expansion and contraction of the rotating blades is within 5 mm in other claims including electromagnetic force. Lacks. Among them, the ring with protrusions bonded and fixed to the blade tip of the rotor blade of claim 6 does not have a mechanism of holes and protrusions to cope with the small contraction that other methods of Patent Document 4 have. The outer peripheral part of the ring with protrusions and the inner peripheral part on the shroud side are in contact with each other by ball bearings. However, if the rotary blade is long and has a diameter of 20 m (rotation radius 10 m), the rotary blade Extends greatly due to centrifugal force. For this reason, even if the blade tips of the rotor blades are connected by an annulus and the effect can be reduced, the blade length and the diameter of the annulus are expanded and contact with the shroud is unavoidable and cannot be rotated. . Even if a new bearing is inserted between the ring and the shroud, it is possible that the bearing is pressed to be unable to rotate or to be crushed. Further, the expansion and contraction due to the temperature rise and fall is likely to have a more serious effect because not only the blades of the rotor blades but also the ring itself. In addition, if the blade of the rotor blade is long, vibration during rotation and standing waves derived from the vibration may be generated.In the worst case, the joint between the ring and the blade may be destroyed, or the ring itself may be damaged. It can also be crushed. Therefore, the ducted fan using electromagnetic force based on claim 6 of Patent Document 4 can be used when the diameter is 1.2 m (rotation radius 0.6 m) or less, as assumed in paragraph 0014 of the specification. However, it cannot be used with rotor blades having a large diameter (rotating radius).

Patent Document 5 in which the driving principle of the rear motor is applied to the wing tip, and Patent Document 2 and Patent Document 4 in which the driving principle of the linear motor is applied to the wing tip (including a rotating duct and an annulus) It is transmitted to the aircraft via a shroud covering the rotor blades. For this reason, as shown in FIG. 50, there is no problem even if the lift force is generated largely and deviated in the vicinity of the blade tip of the rotor blade. Therefore, in the conventional helicopter, the pitch angle of the blade tip having a high airspeed is as close as possible to 0 °, and conversely, the pitch angle of the blade center having a low airspeed is about 15 °, and the lift force of the entire rotor blade is increased. However, in Patent Document 2, Patent Document 4 and Patent Document 5, this is not necessary, and it is most efficient over the entire blade of the rotating blade including the blade tip. It is possible to adopt a pitch angle that can generate lift. Therefore, the pitch angle may be constant as shown in FIG. 50. For example, the entire area can be created at 7 °. In this way, by making the entire area of the rotor blade a pitch angle that can obtain the optimum angle of attack, the same amount of lift generated by the rotor blade of a conventional helicopter can be rotated with a much smaller diameter (turning radius). Can be realized with wings.

Patent Document 2 can obtain an action point based on the driving principle of a linear motor over the entire circumference of the blade tip, and can cope with expansion and contraction of a blade due to centrifugal force or temperature change even in a large rotating blade having a long blade. In addition, it has a mechanism that can suppress the occurrence of blade drooping during rotation, vibration during rotation, and generation of standing waves, and has an excellent effect of generating large lift and propulsive force even with a small diameter (rotation radius). However, when the rotating wing with a rotating duct type shroud of Patent Document 2 is attached to both sides of an aircraft body without attaching a feathering hinge and operated as a lift generating device, the rotation just before takeoff The through-flow velocity effect (induced flow effect), which is a lateral movement accompanied by vibration caused by the wing lift imbalance, is to install the rotor blades with a rotating duct type shroud at symmetrical positions on both sides of the fuselage. Will be offset by the aircraft and will not be affected, but the transition lift, another effect of lift imbalance, will occur as the aircraft begins to move forward and will be noticeable around 22 km / h (about 12 kt). Appear in The transfer lift, body lift the front (nose) by raising the head of the body because they act on (nose-up) direction, inhibits the increase in speed. For this reason, when using as a lift generator without attaching a feathering hinge to the rotating duct type shroud rotor blade of Patent Document 2, the entire rotating duct type shroud rotor blade is tilted forward (with reference to the horizontal). It must be used with a tilting device that can take a negative depression angle in some cases. In order to suppress the transfer lift by tilting the entire rotor blade with a rotating duct type shroud using the tilt device, it is necessary to tilt up to the pitch angle of the blade. Therefore, in the case of a rotor blade with a rotating duct type shroud created with a pitch angle of 7 °, a tilt device capable of tilting the entire rotor blade with a rotating duct type shroud forward to a maximum of 7 ° is required. The use of a rotating duct type shroud rotor with no accompanying entails significant energy loss in forward flight.

Patent Document 4 and Patent Document 5 are examples in which a rotor blade that applies a driving principle of a linear motor to a blade tip or a blade tip portion is applied to a tail rotor of a conventional single rotor helicopter. Further, Patent Document 1 is an implementation of an aircraft in which the rotating duct type shroud-equipped rotor blade of Patent Document 2 is integrated with a rapid wind direction changing device to form a rapid air volume generating wind direction changing device attached to the side surface or side wall of the fuselage. It is an example. When the rotary duct type shroud-equipped rotor blade of Patent Document 2 is used as a lifting device without a feathering hinge, the rotating blade may be tilted forward by an angle that can eliminate or reduce the influence of the transfer lifting force. Although a tilting device that can be used is necessary, in Patent Document 1, since the rotating duct type shroud-equipped rotor blade of Patent Document 2 is attached to a rapid wind direction changing device capable of arbitrary tilting, it is operated in accordance with speed and relative wind. Tilt (in the calculation in the figure, a depression angle of −2 to −7 ° when the horizontal plane is used as a reference) can be given to the rotating duct type shroud-equipped rotor blade. Therefore, in patent document 1, since the nose-up by the transfer lift at the time of advancing can be suppressed, the factor which inhibits speed can be removed and it can fly at high speed.

Patent Document 3 has a mechanism in which a fan engine is mounted on the inside of a double rack and pinion type cylinder device and tilted in two axes, and the direction of the fan engine is 360 ° around the entire circumference. The rack and pinion type cylinder device can increase the rotation speed, but has a limited operating range depending on the length of the rack gear. Therefore, even if it is effective when tilting at a high speed in a narrow range, use in a wide range exceeding 360 ° or 360 ° on the entire circumference may slow down the rotation speed or cause a lack of force. It is expensive and not suitable for use.

In Patent Document 6, two rotor blades are attached in total, one at the front of the aircraft and one at the rear, based on the forward direction at the time of cruising. A conventional helicopter that is driven by a driving force and the generated lift is transmitted to the airframe via the rotating shaft of the blade center and flies, and is a conventional tandem helicopter, for example, V-107 (Bartle) and multi-rotor aircraft such as CH-47 (Chinook) are not different in flight characteristics and do not have particularly excellent effects. However, the conventional rotor blade of Patent Document 6 is replaced with the rotor blade with a rotating duct type shroud of Patent Document 2 and is combined with the biaxial tilt device of Patent Document 3 or Patent Document 7 to create a patent. Document 6 can constitute a new aircraft having a different flight system from the present invention.

Patent No. 36777748 (Claim 1, Claim 2, FIG. 1, FIG. 2, FIG. 3, FIG. 4, FIG. 5, FIG. 6, FIG. 7, FIG. 8, FIG. 9, FIG. 9, FIG. 11, FIG. 15, FIG. 16) Japanese Patent No. 3595988 (Claim 1, FIG. 1, FIG. 3, FIG. 5, FIG. 8) JP 2003-137192 A (Claim 1, Claim 2, Claim 5, FIG. 1, FIG. 2, FIG. 5, FIG. 6, FIG. 8, FIG. 9, FIG. 10, FIG. 11, FIG. 12) JP 2001-097288 (Claims 6, 0042, 0043, 0044, 0045, FIGS. 7 and 8) JP-A-7-205897 (Claims 1, 0001, 0008, FIGS. 1, 2, and 3) JP-A-7-125696 (Claim 1, Claim 2, Claim 3, Claim 4, Claim 5, 0015, 0021, 0026, 0031, FIG. 1, FIG. 2, FIG. 3, FIG. 4, FIG. FIG. 6, FIG. 7, FIG. 8) Japanese Patent Application No. 2004-227323 (Claim 2, FIG. 5, FIG. 6, FIG. 7, FIG. 8, FIG. 9, FIG. 12) British Patent No. 1228469 (Description, Claims 1, 2 and 3) US Pat. No. 3,383,074 (specification) Michael J.M. Hirschberg, Thomas Muller, Alexis Rocher, “FRENCH LOW-SPEED V / STOL CONCESS OF THE TWENTIETH CENTURY”, [online], [August 8, 2005 search], Internet <URL: http: // www vtol. org / pdf / stofl-58. pdf:> Michael J.M. Hirschberg, “The American Helicopter”, [online], [August 8, 2005 search], Internet <http: // www. iasa. com. au / foldersPublications / pdf_library / ospreydfs / The% 20American% 20Helicopter. pdf>

An aircraft that attaches a rotor blade with a shroud to the fuselage to generate lift and propulsion and flies, and has a rapid air volume generation wind direction change device that combines a rotary duct type rotor blade with a shroud and a rapid wind direction change device of Patent Document 2. Although it is as patent document 1 attached to the side surface, as for the aircraft of patent document 1, the rapid air volume generation | occurrence | production direction change apparatus extended to the side of the body greatly, occupied a place, and it was also difficult to fold. The present invention makes it possible to store the rotary duct type shroud rotor blade of Patent Document 2 on the bottom plate, and when the aircraft descends to the ground and stops the rotary duct type shroud rotor blade, the space is folded and occupied. If you put it out from the bottom plate and exhibit it, the rotating surface of the rotating wing with rotating duct type shroud will stand upright with respect to the fuselage, and it will be able to produce lift or propulsion, and you can fly the aircraft It is a problem.

In the present invention, by allowing the rotating duct type shroud rotor blade of Patent Document 2 to be stored in the bottom plate that connects the airframe and the shroud rotor blade, the area occupied by the airframe during ground parking can be reduced, and from the bottom plate. An aircraft with a rotating duct type shroud-equipped rotor attached to the fuselage by creating a mechanism that allows the rotating surface of the rotating duct type shroud rotor to stand upright easily and generate lift and propulsion when pulled out Can be facilitated.

In the present invention, a rotating duct type shroud-equipped rotor blade that can efficiently generate a driving force at the blade tip of the rotor blade is used. Therefore, even with a remarkably small diameter (turning radius) compared to a conventional helicopter rotor blade, Can generate lift. The rotary duct type shroud rotor that can generate sufficient lift or propulsion with a small diameter (rotation radius) of the rotor can be sized to easily fold on the side of the aircraft body. In addition, the hydraulic piston device, the electric worm gear device, or the pantograph mechanism can be stored in the bottom plate that connects the fuselage and the rotor blade with the rotating duct type shroud, or can be extended from the bottom plate. There is an advantage in reducing the occupied area when parked on the ground, when loading on another transportation, for example, the air ferry of Patent Document 1, or when using a marine ferry or land transportation. In particular, if you have created a small wireless controller equipped with autonomous navigation equipment with a small one, you can fold the rotating wing with a shroud and store it on the bottom plate, so that it is close to a one-box car, for example. Can also be transported by simple vehicles.

In the present invention, the rotating duct type shroud-equipped rotor blade of Patent Document 2 or the ducted fan using electromagnetic force of Claim 6 of Patent Document 4 capable of efficiently applying a driving force to the entire circumference of the blade tip portion is used. . Of these, the rotating duct type shroud-equipped rotor blade of Patent Document 2 has a mechanism that can cope with expansion of the blade of the rotating blade and expansion of the rotating duct itself at the contact portion between the shroud at the blade end and the rotating duct. In addition, there is a rotation support part in the middle of the blade of the rotor blade to suppress the vibration of the blade and the generation of standing waves, and to prevent the blade of the rotor blade from drooping when stopped during parking Therefore, a gap (gap) between the electromagnet disposed on the inner peripheral portion of the shroud and the permanent magnet disposed on the outer peripheral portion of the rotating duct is kept constant, and is generated between the electromagnet and the permanent magnet. Since the suction force and the repulsive force can be generated stably, it can be used at any diameter (rotation radius). Therefore, in principle, the present invention employs the rotating duct type shroud-equipped rotor blade of Patent Document 2 with any diameter (rotation radius). The other ducted fan using electromagnetic force disclosed in Patent Document 4 is not suitable for using a long blade in a horizontal position. Therefore, as assumed in paragraph 0014 of the specification, the diameter is 1.2 m (the radius of rotation is 0). .6m) May be used in the following cases.

In the present invention, a rotating duct type shroud rotor blade of Patent Document 2 is attached to an aircraft body via a bottom plate that enables storage and exhibition. Therefore, when rotating the rotor blades with a rotating duct type shroud, the rotating surface is stored in the bottom plate in parallel with the aircraft, and the rotating surface is positioned upright with respect to the aircraft when pulled out from the bottom plate and extended. Thus, lift and propulsion can be generated, and the aircraft can fly freely.

The bottom plate (with tilt device) (with no tilt device) (6 or 7) that can store or exhibit the rotating duct type shroud rotor blade (3 or 4) used in the present invention is attached to the aircraft body (1). When viewed from the side surface direction of the airframe (1) in the mounted state, the bottom plate (with tilt device) (6) has a bottom plate mounting shaft (8) at the upper part behind. At the bottom of the bottom plate (with tilt device) (6), there is a tilt device (9) that can tilt the bottom plate (with tilt device) (6) itself around the bottom plate mounting shaft (8). The tilt device (9) has a hydraulic piston or worm gear rod (10) in a shape parallel to the side surface of the airframe (1), and the end of the rod (10) is a protrusion of the airframe (1). Is omitted). By expanding and contracting this rod (10), the entire bottom plate (with tilt device) (6) is moved forward about 15 ° (an inclination angle of 15 ° or −15 °) and backward 15 ° (an elevation angle of 15 ° or + 15 °). ) Tilt to a degree.

The tiltable range of the tilting device (9) used in the bottom plate (with tilting device) (6) of the present invention is about −15 ° to + 15 °. This value is larger than necessary when dealing only with the transfer lift, but it has a shroud-equipped rotor blade (2) with a bottom plate that enables storage and exhibition books dedicated to propulsion generation. In the case of no embodiment, it is initially a depression angle of about −12 ° until the forward speed can be obtained by moving the shroud-equipped rotor blade (2) with the bottom plate that enables storage and exhibition at the time of takeoff. Therefore, the tilt is set to about −15 °. Further, in the case of sudden stop, the elevation angle may be up to about 15 °, so that it is about + 15 °. The tilt device (9) is required when the rotor blade with shroud (2) with a bottom plate that enables storage and exhibition is used as a lifting device, and when it is used exclusively for propulsion. Is an unnecessary device and may be removed. On the contrary, when used for both lift and propulsion as required, quick rotation is required for the entire circumference. Therefore, in this case, it is used by being mounted on the rapid wind direction changing device of Patent Document 1.

The structure of the bottom plate (with tilt device) (without tilt device) (6 or 7) has a rotary blade extension shaft (12) to which a rotary blade with a rotating duct type shroud is attached at the upper part inside, and a lower part inside The base part of the hydraulic piston device (13), the electric worm gear device (14), or the pantograph (15), which is required when the rotating duct type shroud-equipped rotor blades are housed in the bottom plate and when it is expanded. Has an action point bottom shaft (16) for mounting.

When the storage and expansion of the rotor blades with shrouds (2) with the bottom plate enabling storage and expansion according to the present invention are performed by the hydraulic piston device (13) and by the electric worm gear device (14) In the case of the rotor blade with a rotating duct type shroud (when using a hydraulic piston device or an electric worm gear device) (3) when viewed from the side of the fuselage (1) in the retracted state, the upper part of the outer periphery of the shroud Has an exhibition book support part (5), and has an action point grip shaft (for central part) (17) in the central part. In this case, the base part of the hydraulic piston device (13) or the electric worm gear device (14) is the action point bottom shaft (16), and the part that is the action point (tip part) is the action point grip shaft (center). When the hydraulic piston device (13) or the electric worm gear device (14) is contracted by being slidably connected to the component (17), the rotary vane with shroud (hydraulic piston device or electric worm gear device is used) When (3) is stored in the bottom plate (with tilt device) (without tilt device) (6 or 7) and extended, the rotating duct type rotor blade with shroud (when using hydraulic piston device or electric worm gear device) (3) The plane of rotation is extended to a position upright with respect to the airframe (1) so that the aircraft can fly.

When the storage and exhibition of the rotor blades with shrouds (2) with the bottom plate enabling the storage and exhibition books according to the present invention is carried out with personnel and pantographs, the rotor blades with shroud of the rotating duct type (use of pantographs) When (4) is viewed from the side of the fuselage (1) in the retracted state, it has an exhibition book support part (5) at the upper part of the outer periphery of the shroud and the action point grip at the lower part. It has a shaft (for end) (18). The pantograph (15) used for the storage and exhibition book has one base portion as the action point bottom axis (16) and the other action point portion (the tip portion) as the action point grip axis (for the end portion). Connect to (18) in a slidable state. Rotating duct type shroud-equipped rotor blades (when using pantograph) (4) When storing and expanding, pantograph (15) is in the retracted position with personnel having action point grip shaft (for end) (18) Arrange appropriate personnel for folding and taking out at the exhibition location. The rotating duct type shroud-equipped rotor wing (when using a pantograph) (4) is also in a state where the aircraft can fly, with the rotating surface standing upright with respect to the aircraft (1), Become.

An aircraft flying with a shroud-equipped rotor wing (2) with a bottom plate that enables storage and exhibition book according to the present invention attached to the side or side wall of the fuselage (1) is symmetrical on the side of the fuselage (1). It can be created if there are two in total, one on each side and a total of both left and right sides. However, if it is possible to fly sufficiently freely, two or more of the present invention capable of generating lift on one side, one or more of the present invention capable of generating propulsive force, and generation of lift on both left and right sides It is desirable that four or more of the present invention for mounting and six or more of the present invention for generating propulsive force be attached in total on both the left and right side surfaces.

FIGS. 22 to 30 show that the rotor blades with shrouds with the bottom plate that enable storage and exhibition of the present invention are used as lifting devices, two on each side surface (wall) of the fuselage, and the direction change and propulsive force. This is an embodiment of an aircraft using six units in total on the left and right side surfaces (walls), one on each side surface (wall) of the aircraft as a device.

FIGS. 31 to 39 show one side of the fuselage as a device that uses the shroud-equipped rotor blades with the bottom plate that enables storage and exhibition of the present invention as a device for changing the forward speed and direction in combination with the lifting device. This is an embodiment of an aircraft in which two units are attached to the left and right side surfaces (walls) one by one on the wall, and the two units are operated with a tilt device to fly.

FIGS. 40 to 48 show an embodiment of the present invention as a device for using a shroud-equipped rotor blade with a bottom plate that enables storage and exhibition of books according to the present invention as a device for use in advancing speed and direction change (see FIG. This is an example of an aircraft in which four units are attached to the left and right side surfaces (walls) in total, and the four units are operated by a tilt device and fly.

The shroud-equipped rotor blade with a base plate that enables storage and exhibition of the present invention is simple in structure and has little occupied space when parked, so when storing or transporting using other transportation means It is effective. In particular, medium-sized ones can save the terminal space that should be owned by carriers who use the present invention as aerial trucks instead of ground trucks, and small ones can be stored in the gardens and garages of private homes. The drone can be stored in a space like a one-box car, so it can be used in many places.

It is the figure seen from the side of an airframe, when the baseplate of this invention is attached to an airframe. It is the figure of the component which looked at the back side of the baseplate of this invention from the body inside side. It is the figure which attached the bottom plate of this invention to the body, extended | stretched the rod of the tilt apparatus in the lower part to one side, and inclined the bottom plate of this invention to one side. FIG. 4 is a view in which the bottom plate of the present invention is attached to the airframe, the rod of the tilt device at the bottom is extended to the other side opposite to FIG. 3, and the bottom plate of the present invention is tilted to the other side. When the present invention is used as a propulsive force device, it is a view in which a tilt device that is not required is removed. The rapid wind direction changing device of Patent Document 1 is used because the shroud-equipped rotor blade with a bottom plate that enables storage and exhibition book according to the present invention can be easily switched to either a lifting device or a propulsion device. It is a figure at the time of attaching and preparing a baseplate. FIG. 3 is a front view of a rotating duct type shroud-equipped rotor blade when a hydraulic piston device or an electric worm gear device is used for storing or exhibiting the rotating duct type shroud-equipped rotor blade used in the present invention. FIG. 3 is a front view of a rotating duct type shroud-equipped rotor blade when the rotating duct type shroud-equipped rotor blade used in the present invention is manually stored by a pantograph mechanism. It is a figure of the hydraulic piston apparatus which stores and exhibits a rotary duct type shroud rotary blade used in the present invention. It is a figure of the electric worm gear apparatus which stores and exhibits the rotary duct type shroud-equipped rotor blade used in the present invention. It is a figure at the time of seeing from the side of an airframe in the state where the whole in the case of storing and exhibiting a rotary duct type shroud-equipped rotor blade used in the present invention by a hydraulic piston device. It is a figure at the time of seeing from the side of the body in the state which stored the whole and the case where the rotary wing with a rotating duct type shroud used by this invention and an exhibition book are performed with an electric worm gear apparatus. It is a figure of the pantograph in the case of performing storage and an exhibition book with a human power and a pantograph among the rotary duct type shroud rotary blades used in the present invention. It is a figure at the time of seeing from the side of the body in the state which stored the whole and the case where the rotation duct type shroud-use rotary blade used in the present invention is stored with human power and a pantograph. It is the figure which looked at the baseplate of this invention from the upper direction of the body in the state which accommodated the rotary blade with a rotating duct type shroud. It is the figure which looked at the baseplate of this invention from the upper direction of the body in the state which extended the rotary blade with a rotating duct type shroud. In this case, the storage and exhibition book uses a hydraulic piston device. It is the figure which looked at the baseplate of this invention from the upper direction of the body in the state which extended the rotary blade with a rotating duct type shroud. In this case, the storage and exhibition book uses an electric worm gear device. It is the figure which looked at the baseplate of this invention from the upper direction of the body in the state which extended the rotary blade with a rotating duct type shroud. In this case, storage and exhibition books use pantographs. It is the figure which looked at the baseplate of this invention from the front of the body in the state which extended the rotary blade with a rotating duct type shroud. In this case, the storage and exhibition book uses a hydraulic piston device. It is the figure which looked at the baseplate of this invention from the front of the body in the state which extended the rotary blade with a rotating duct type shroud. In this case, the storage and exhibition book uses an electric worm gear device. It is the figure which looked at the baseplate of this invention from the front of the body in the state which extended the rotary blade with a rotating duct type shroud. In this case, storage and exhibition books use pantographs. The shroud-equipped rotor blade with a base plate that enables storage and exhibition book according to the present invention, three as a lifting device on one side, one as a propulsion device, lift on both sides FIG. 2 is a view of an aircraft in a state of being viewed from the front front of the fuselage in the case of flying using a total of six units, four as devices and two as propulsion devices. The shroud-equipped rotor blade with a base plate that enables storage and exhibition book according to the present invention, three as a lifting device on one side, one as a propulsion device, lift on both sides FIG. 5 is a view of an aircraft in an expanded state as viewed from above the fuselage when flying using a total of six units, four as devices and two as propulsion devices. The shroud-equipped rotor blade with a base plate that enables storage and exhibition book according to the present invention, three as a lifting device on one side, one as a propulsion device, lift on both sides FIG. 5 is a view of an aircraft in a state of being viewed from the side of the fuselage in the case of flying using a total of six units, four as devices and two as propulsion devices. The shroud-equipped rotor blade with a base plate that enables storage and exhibition book according to the present invention, three as a lifting device on one side, one as a propulsion device, lift on both sides It is the figure which is flying horizontally using a total of six sets of four as a device and two as a propulsion device. When this aircraft flies horizontally, the shroud-equipped rotor blade with the bottom plate that enables storage and exhibition book used as the lifting device of the present invention increases the forward speed by suppressing nose-up caused by the transfer lift. Therefore, it fly with a depression angle of -2 to -7 degrees. The shroud-equipped rotor blade with a base plate that enables storage and exhibition book according to the present invention, three as a lifting device on one side, one as a propulsion device, lift on both sides When using a total of 6 units, 4 units and 2 units as propulsion devices, the aircraft that is mainly specialized in propulsion is required to stop and turn when the aircraft is moving forward. To do. However, when performing a sudden stop or a sudden turn, the device that generates lift also gives an elevation angle of up to about 15 °, and performs a sudden stop or a sudden turn together with a device dedicated to propulsion. . The shroud-equipped rotor blade with a base plate that enables storage and exhibition book according to the present invention, three as a lifting device on one side, one as a propulsion device, lift on both sides When flying using a total of 6 units, 4 units and 2 units as propulsion devices, when an obstacle on the ground suddenly appears ahead, it is the most effective way to avoid upwards. The elevation angle is given to the two units on both sides of the front to obtain the maximum output. Then, the aircraft may have a transition lift effect, and may suddenly nose up and turn up to avoid it. The shroud-equipped rotor blade with a base plate that enables storage and exhibition book according to the present invention, three as a lifting device on one side, one as a propulsion device, lift on both sides A front view of an aircraft using 4 units as a device and 2 units as a propulsion device when parked with a rotating wing with a rotating duct type shroud stored in the bottom plate is there. The shroud-equipped rotor blade with a base plate that enables storage and exhibition book according to the present invention, three as a lifting device on one side, one as a propulsion device, lift on both sides Plane seen from above when an aircraft that uses 4 units as a device and 2 units as a propulsion device stores a rotor blade with a rotating duct type shroud in the bottom plate and parks on the ground FIG. The shroud-equipped rotor blade with a base plate that enables storage and exhibition book according to the present invention, three as a lifting device on one side, one as a propulsion device, lift on both sides It is a side view when the aircraft which uses a total of 6 units | sets, 4 units | sets as a device and 2 units | sets as a propulsion apparatus, has parked on the ground, storing the rotary wing with a rotating duct type shroud in a baseplate. The rotor blades with shrouds with the bottom plate that enables storage and exhibition book according to the present invention are used as a forward and direction changing device in combination with a lifting device, and two in total on the left and right, one on each side of the aircraft. FIG. 3 is a front view of an aircraft in a state where rotary wings with a rotating duct type shroud are extended when viewed from the front of the fuselage. The rotor blades with shrouds with the bottom plate that enables storage and exhibition book according to the present invention are used as a forward and direction changing device in combination with a lifting device, and two in total on the left and right, one on each side of the aircraft. FIG. 3 is a plan view of an aircraft in a state where rotary wings with a rotating duct type shroud are extended when viewed from above the fuselage. The rotor blades with shrouds with the bottom plate that enables storage and exhibition book according to the present invention are used as a forward and direction changing device in combination with a lifting device, and two in total on the left and right, one on each side of the aircraft. FIG. 5 is a side view of a rotating duct type shroud-equipped rotor blade in the case of flying. The rotor blades with shrouds with the bottom plate that enables storage and exhibition book according to the present invention are used as a forward and direction changing device in combination with a lifting device, and two in total on the left and right, one on each side of the aircraft. FIG. 5 is a side view showing a rotating duct type shroud-equipped rotating wing and flying an aircraft in a horizontal flight. In this case, by tilting the present invention in the forward direction, the transfer lift is suppressed and the propulsion force for the forward movement is obtained to fly. The rotor blades with shrouds with the bottom plate that enables storage and exhibition book according to the present invention are used as a forward and direction changing device in combination with a lifting device, and two in total on the left and right, one on each side of the aircraft. In the case of flying, the rotating duct type shroud-equipped rotating wing is extended, and when the aircraft flies, the present invention is tilted backward to stop or change the direction. The rotor blades with shrouds with the bottom plate that enables storage and exhibition book according to the present invention are used as a forward and direction changing device in combination with a lifting device, and two in total on the left and right, one on each side of the aircraft. FIG. 6 is a plan view of the aircraft as viewed from above, wherein the left side surface of the present invention is tilted forward, the right side surface of the present invention is tilted backward, and the aircraft is rotated to the right. The rotor blades with shrouds with the bottom plate that enables storage and exhibition book according to the present invention are used as a forward and direction changing device in combination with a lifting device, and two in total on the left and right, one on each side of the aircraft. FIG. 5 is a front view of the rotary duct type shroud-equipped rotor blade stored in the bottom plate and viewed from the front when parked on the ground. The rotor blades with shrouds with the bottom plate that enables storage and exhibition book according to the present invention are used as a forward and direction changing device in combination with a lifting device, and two in total on the left and right, one on each side of the aircraft. FIG. 5 is a plan view of the rotary duct type shroud-equipped rotor blades stored in the bottom plate and viewed from above when parked on the ground. The rotor blades with shrouds with the bottom plate that enables storage and exhibition book according to the present invention are used as a forward and direction changing device in combination with a lifting device, and two in total on the left and right, one on each side of the aircraft. FIG. 5 is a side view when the rotary duct type shroud-equipped rotor blades are stored in the bottom plate and parked on the ground when flying in the air. The rotor blades with shrouds with the bottom plate that enables storage and exhibition book according to the present invention are used as a forward and direction changing device in combination with a lifting device, and four in total on the left and right, two on each side of the aircraft. FIG. 3 is a front view of an aircraft in a state where rotary wings with a rotating duct type shroud are extended when viewed from the front of the fuselage. The rotor blades with shrouds with the bottom plate that enables storage and exhibition book according to the present invention are used as a forward and direction changing device in combination with a lifting device, and four in total on the left and right, two on each side of the aircraft. FIG. 3 is a plan view of an aircraft in a state where rotary wings with a rotating duct type shroud are extended when viewed from above the fuselage. The rotor blades with shrouds with the bottom plate that enables storage and exhibition book according to the present invention are used as a forward and direction changing device in combination with a lifting device, and four in total on the left and right, two on each side of the aircraft. FIG. 5 is a side view of a rotating duct type shroud-equipped rotor blade in the case of flying. The rotor blades with shrouds with the bottom plate that enables storage and exhibition book according to the present invention are used as a forward and direction changing device in combination with a lifting device, and four in total on the left and right, two on each side of the aircraft. FIG. 5 is a side view showing a rotating duct type shroud-equipped rotating wing and flying an aircraft in a horizontal flight. In this case, by tilting the present invention in the forward direction , the transfer lift is suppressed and the propulsion force for the forward movement is obtained to fly. The rotor blades with shrouds with the bottom plate that enables storage and exhibition book according to the present invention are used as a forward and direction changing device in combination with a lifting device, and four in total on the left and right, two on each side of the aircraft. In the case of flying, the rotating duct type shroud-equipped rotating wing is extended, and when the aircraft flies, the present invention is tilted backward to stop or change the direction. The rotor blades with shrouds with the bottom plate that enables storage and exhibition book according to the present invention are used as a forward and direction changing device in combination with a lifting device, and four in total on the left and right, two on each side of the aircraft. As a useful means to avoid upwards when an obstacle on the ground suddenly appears when an aircraft flies, a rotor duct with a rotating duct type shroud is exhibited. The elevation angle is given to the two units to obtain the maximum output. Then, the aircraft may have a transition lift effect, and may suddenly nose up and turn up to avoid it. The rotor blades with shrouds with the bottom plate that enables storage and exhibition book according to the present invention are used as a forward and direction changing device in combination with a lifting device, and four in total on the left and right, two on each side of the aircraft. FIG. 6 is a front view of the rotary duct type shroud-equipped rotor wing when viewed from the front when retracted and parked on the ground. The rotor blades with shrouds with the bottom plate that enables storage and exhibition book according to the present invention are used as a forward and direction changing device in combination with a lifting device, and four in total on the left and right, two on each side of the aircraft. FIG. 6 is a plan view of the rotary duct type shroud-equipped rotor wing when viewed from above and viewed from above when parked on the ground. The rotor blades with shrouds with the bottom plate that enables storage and exhibition book according to the present invention are used as a forward and direction changing device in combination with a lifting device, and four in total on the left and right, two on each side of the aircraft. FIG. 6 is a side view of the rotary duct type shroud-equipped rotor blades when parked and parked on the ground. It is the figure which looked at the rotary blade in rotation of the conventional type helicopter from the side. Conventional helicopter rotors use very heavy blades and gain lift by being able to maintain an inverted conical blade shape during flight. At this time, if a remarkably large lift is generated at the blade tip, the blade warps and the lift is reduced, so the blade is twisted to reduce the lift at the blade tip. The ideal form is that the lift generated in various places up to the heart is uniform. Further, since the blade also has a role of a weight during rotation and is very heavy, it is extremely difficult to increase the number of the blades in order to increase the lift in terms of increase in the weight of the fuselage and engine capacity. It is the figure of the partial cross section which looked at the rotary blade with a rotating duct type shroud used for this invention from the side. The rotary duct type rotor blade with a shroud brings the rotor duct at the blade tip into contact with the shroud via a bearing, and the lift generated by the rotor blade is transmitted from the rotor duct at the blade tip to the airframe via the shroud. . For this reason, even if an extremely large lift is generated on the blade tip, there is no adverse effect such as bending of the blade. Also, the weight of the blade does not serve as a weight unlike conventional helicopters, so a very light material can be used. Therefore, with respect to the pitch angle of the blade, a pitch angle that can create an angle of attack that can generate lift most efficiently during flight can be selected over the entire blade, and there is a problem even if the number of blades is increased. Because there is no large diameter, a large lift can be generated with a small diameter (rotating radius).

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 Airframe 2 Rotor blade with shroud with bottom plate enabling storage and exhibition book 3 Rotor blade with rotating duct type shroud (when using hydraulic piston device or electric worm gear device)
4 Rotating wing with rotating duct type shroud (when using pantograph)
5 Exhibition book support 6 Bottom plate (with tilt device)
7 Bottom plate (no tilt device)
8 Bottom plate mounting shaft 9 Tilt device 10 Rod 11 Rapid air direction changing device 12 Rotary blade extension shaft 13 Hydraulic piston device 14 Electric worm gear device 15 Pantograph 16 Action point bottom shaft 17 Action point gripping shaft (for central part)
18 Action point grip shaft (for end)
19 Swash plate 20 Blade 21 Rotating duct 22 Shroud 23 Direction and size of lift

Claims (2)

Drives by generating an attractive force and a repulsive force between the electromagnet disposed on the inner periphery of the shroud and the permanent magnet disposed on the outer periphery of the blade tip (including rotating duct and ring) In the rotor blade with a rotating duct type shroud having the driving principle of the linear motor at the blade tip ,
(1) It has a shaft (hereinafter referred to as a bottom plate mounting shaft) on the back for mounting it in a slidable state on the fuselage, and a rotary wing with a rotating duct type shroud is housed in the upper part of the front (front) surface. A shaft that serves as a fulcrum for rotation during exhibition or exhibition (hereinafter referred to as a rotary blade exhibition axis), and a lower part is connected to a hydraulic piston device, an electric worm gear device, or the base of a pantograph to support storage or exhibition (Hereinafter referred to as a bottom axis of action point).
(2) It has a part (hereinafter referred to as an exhibition book support part) into which the rotating blade extension shaft of the bottom plate is slidably fitted at the end of the outer peripheral part, and the storage and exhibition book is a hydraulic piston device or an electric worm gear device. In the case of the above, a shaft for mounting one end of a hydraulic piston device or an electric worm gear device in a slidable state at the center of the outer periphery having the maximum diameter when viewed from the side facing the front (front) surface (hereinafter referred to as a shaft) , It has an action point grip axis (for the central part), and when storing and exhibition books with human power and pantographs, one end of the pantograph can slide on the opposite end of the outer periphery of the exhibition book support part Rotating duct type shroud-equipped rotor blade having a shaft (hereinafter referred to as an action point gripping shaft (for an end)) for mounting in a stable state.
(3) When one base portion of the device is slidably connected to the bottom shaft of the working point in the bottom plate and the device is a hydraulic piston device or an electric worm gear device, the other tip is connected to the rotating duct type shroud. When the device is a pantograph, the other tip is slid to the action point gripping shaft (for the end). A hydraulic piston device, an electric worm gear device or a pantograph for storing and expanding the rotating duct type shroud-equipped rotor blades on the bottom plate by connecting and expanding in a possible state.
(4) When the rotating duct type shroud-equipped rotor blade is used as a device for generating lift, it is attached to the lower part of the bottom plate outer part, and one end of the device is brought into contact with the projection of the fuselage to expand and contract the entire bottom plate. A tilt device that can feed out a rod tilted in a range of −15 ° to + 15 ° by a hydraulic piston or an electric worm gear.
It consists, when storing the rotating winged rotating duct system shroud bottom plate, rotating winged rotating duct system shroud is disposed within the bottom plate in a state parallel to the rotation plane relative to the body reduces the area occupied by the aircraft However, when exhibiting, the rotating wing with a rotating duct type shroud enables the storage and exhibition book, where the rotating surface is upright with respect to the aircraft and can generate lift or propulsion. A rotor blade with a shroud with a fixed bottom plate. One or more of the rotor blades with shrouds with the bottom plate enabling the storage and exhibition of claim 1 on one side or side wall of the fuselage when the forward direction at the time of cruise of the aircraft is used as a reference, An aircraft that attaches two or more side surfaces or side walls in a symmetrical position in total and generates lift during cruise to fly.

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