JP2006021733A - Vertical taking-off and landing machine installing rapid wind quantity generation wind direction changing device of double inversion two-axis tilt as device for lift and propulsion of machine body and using it as steering means - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide an aircraft having an efficient motor capable of saving energy and capable of speedily and accurately changing direction of blowing-out of a rotor such as a propeller not only on a vertical face but also on a horizontal face and realizing easy steering of an automobile running on the ground in spite of the fact that it is the aircraft in a vertical taking-off and landing machine having a rotor such as a blade and a propeller and obtaining lift when taking off and landing and thrust when cruising. <P>SOLUTION: In the motor of the propeller for generating lift when the vertical taking-off and landing machine takes off and lands and thrust when cruising, the rapid wind quantity generation wind direction changing device of double inversion two-axis tilt having the principle of driving a linear motor efficiently by saving energy and realizing tilt of two axes at high speed is adopted and operated to change wind quantity and direction of blowing-out freely, speedily, and accurately without limit in the vertical and left and right directions so that the vertical taking-off and landing machine capable of steering a machine body with sense of the automobile running on the ground without operating the complicated blade in steering can be made. <P>COPYRIGHT: (C)2006,JPO&NCIPI

Description

  The present invention integrates a rotating blade with a double reversing shroud having a driving principle of a linear motor and a rapid wind direction changing device capable of rapidly changing the blowing direction with two shafts. By using the rapid airflow generating wind direction change device for lift and propulsion devices of aircraft with wings and propellers or fans (hereinafter referred to as propellers), vertical takeoff and landing and short range takeoff and landing are possible. The present invention relates to the realization of an aircraft that can be easily operated with the same feeling as a running car.

  Patent Document 4, Patent Document 5, Patent Document 7, Patent Document 9 and Non-Patent Document 1 have fixed wings that generate most of the lift during cruising, and have rotor blades such as propellers, This is a vertical take-off and landing aircraft that obtains thrust during cruising. Regarding driving, Patent Literature 5, Patent Literature 7, Patent Literature 9, and Non-Patent Literature 1 are all driven at the center of rotation of a rotor such as a propeller. In Patent Document 4, the driving force and the propulsive force are obtained by the explosive combustion of the jet fuel in the combustion chamber at the center of the rotation of the fan, and the rotor blades such as the propeller are driven. , Consuming enormous energy.

  Regarding driving, Patent Literature 1, Patent Literature 3, Patent Literature 6 and Patent Literature 8 stop the conventional method of connecting power while consuming enormous energy at the center of rotation of a rotor blade such as a propeller. We proposed a mechanism of a rotor blade with a shroud that rotates a rotor blade such as a propeller by applying a linear motor drive principle near the blade tip of the rotor blade that can obtain efficient torque (rotation torque) with the energy of . The driving force of a rotor blade with a shroud, which has a linear motor drive principle, is generated near the blade tip of the rotor blade. Therefore, the magnet that serves as the stator on the shroud side and the blade tip side (including the ring and rotating duct) ), The magnitude of the force generated between the rotor and the magnet and the radius of the shroud determine the magnitude of the rotational torque, so the size of the shroud opening (hereinafter referred to as the aperture) is Larger ones can generate more effective lift and thrust. However, Patent Document 8 does not consider the expansion and contraction of the blade constituting the rotor blade such as a propeller at all, and Patent Document 6 does not consider the expansion and contraction of the blade by considering only two of the centrifugal force and the temperature change. Is not considered for deflection and distortion caused by the weight of the blade when used in a horizontal position, and was originally made assuming a diameter of about 1.2 m (radius 0.6 m) Therefore, it is a rotor blade with a shroud that has a driving principle of a linear motor that can exert an advantageous effect as a large diameter is insufficient to cope with expansion and contraction of the blade etc., but even if the disclosed mechanism is expanded and generalized It is extremely difficult to produce a rotor blade with a shroud having a diameter exceeding about 3 m (radius is about 1.5 m). Patent Document 3 has an electromechanical mechanism that can cope with a large expansion and contraction of the blade in the blade thickness, but has a portion that is vulnerable to a rapid change in the blowing direction. , Without tilting the rotating disk surface, adjusting the lift while changing the angle of attack of the blade at any position on the rotating surface with a sliding device, etc. It is desirable to use in a small environment. Patent Document 1 discloses that the characteristics of a rotor blade with a shroud having a linear motor driving principle that has an advantageous effect as a large diameter is maximized in the middle of the blade. Because it has a rotation support part that suppresses deflection and distortion due to the weight of the blade, and the expansion and contraction of the blade that remains even with the rotation support part is absorbed by the rotation duct, such as the rotation duct absorbs, Theoretically, it is possible to create an infinite large-diameter rotor blade with a shroud, and it can also be used in an environment where a rapid change in the blowing direction is performed.

  Regarding tilt, Patent Document 2, Patent Document 5, Patent Document 7, Patent Document 9 and Non-Patent Document 1 have a mechanism for tilting around one axis on a vertical plane and tilting left and right on a horizontal plane. Not. The tilt method is performed by an electric motor, a gear device, a planetary gear device, a rack and pinion device, a hydraulic device, a rack and pinion type cylinder device, and a rapid wind direction changing device, but the tilt is gradually performed except for the rapid wind direction changing device. For example, in Patent Document 7, 129 to 60 seconds are required for a tilt of 90 degrees, and even a fast one has a speed of several seconds, usually over 1 minute. In Patent Document 4, a two-axis tilt mechanism is realized by a rack and pinion type cylinder device, but in order to overcome the intense gyro effect and change the blowing direction, a large force is required, and the rotation is correspondingly performed. Since the speed is reduced, it is estimated that the tilt of 90 degrees takes several seconds at the fastest, and the tiltable angle range of the rack and pinion type cylinder device is limited by the structure having the cylinder. Therefore, the tilt direction may be limited, and it is difficult to say that it is biaxial, but the wake coming out of the fan engine is extremely hot and long. Even if it is to be protected, it is not possible to carry it in the direction in which the wake will strike the aircraft.

  Regarding the tilt, the rapid wind direction changing device of Patent Document 2 has the same mechanism as the rotor blade with the shroud having the driving principle of the linear motor, so that it exerts a large force against the strong gyro effect and the tilt speed is 90. It has the ability to turn degrees within 1 second, and there is no limit or limit to the angle range that can be tilted on one axis. However, since the shape of the rapid wind direction changing device is disk or cylindrical, it is difficult to create a biaxial tilt device.

  Regarding the maneuverability, Patent Document 4, Patent Document 5, Patent Document 7, Patent Document 9 and Non-Patent Document 1 indicate that the direction of travel is independent even if the thrust of the left and right propellers can be independently changed as a conventional technique. In principle, the wing is operated by operating the wing. In particular, when the direction of travel is greatly changed, the aircraft itself is banked, but when the aircraft is banked and the wing tilts, the wing lift decreases, and the reduced lift is used to operate other parts of the wing, propellers, etc. This involves complicated operations such as the operation of thrust. Among them, since the fan engine of Patent Document 4 has a two-axis tilt, the direction of the fan engine is turned to the left and right while keeping the aircraft horizontal, and the wing lift is not lowered by tilting the aircraft. It is possible to change the direction of travel. However, a fan engine that burns jet fuel is difficult to finely adjust the engine output, has a large time delay with respect to the output up / down instruction, and the blade of the fan engine that rotates at an ultra-high speed includes: Since it is extremely difficult to configure a mechanism that adjusts the airflow by changing the angle of attack, changing the direction of travel of the aircraft, changing the left and right direction of the fan engine and increasing or decreasing the output, replace the rudder of the wing. It cannot be used for maneuvering. That is, even if the operation can be facilitated through a computer, the response speed of the fan engine and the rotation speed of the tilt device cannot be increased, and thus the maneuverability cannot be improved.

  Japanese Patent Application No. 2004-048686 (Claims 1, 4 and 6)   Japanese Patent Application No. 2003-290873 (Claim 1, FIG. 13)   Japanese Patent Application No. 2002-383031 (Claim 1, FIG. 1, FIG. 2, FIG. 4, FIG. 6)   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 2002-205694 A (Claim 1, Claim 2, Claim 3, FIG. 1, FIG. 7, FIG. 8, FIG. 9)   JP 2001-097288 A (Claim 6, FIG. 7, FIG. 8)   JP-T-11-513635 (Claim 1, Claim 2, Claim 7, Claim 10, Claim 11, Claim 23, Claim 24, Claim 26, FIG. 1, FIG. 2, FIG. 3, (FIGS. 6, 9, and 12)   Japanese Patent Laid-Open No. 7-205897 (Claims 1, 0008, FIGS. 1, 2, and 3)   Japanese Patent Laid-Open No. 5-077789 (Claim 1, FIG. 1, FIG. 2)   Wataru Nishikawa, “Aeronautical Modern: Four Tilt Rotors”, [online], “Japan Airlines Newspaper” dated September 21, 2000, [Search April 19, 2004], Internet <URL: http: // / Www2g. bigrobe. ne. jp / ~ aviation / qtr000921. html>

  In a vertical take-off and landing aircraft that has rotor blades such as wings and propellers and obtains lift during take-off and landing and thrust during cruising, it is an energy-saving and efficient prime mover, and the blowing direction of rotor blades such as propellers is horizontal as well as vertical. However, there is a problem to be solved by an aircraft that can be changed quickly and accurately and has an easy maneuverability such as an automobile running on the ground while being an aircraft.

  The propeller prime mover that generates lift during take-off and landing of a vertical take-off and landing aircraft and thrust during cruising uses rotor blades with shrouds that have an energy-saving and efficient linear motor drive principle. A rotor blade with a shroud, which has a linear motor drive principle, is more efficient at larger diameters and can generate the required lift and thrust. However, the vertical take-off and landing aircraft of the present invention can also be used for short-range take-off and landing. The rotation radius of the blade is prepared with a reference of about 2.5 m. As a measure for increasing lift and thrust due to the small diameter, a shroud rotor blade having a linear motor drive principle is a double-reversed shroud rotor blade in which two rotating in opposite directions are superposed in the rotation axis direction. Create and use. The double-reversed shroud-equipped rotor blade can cancel the gyro effect, and is therefore effective when the blowing direction is rapidly changed.

  The tilt device that rotates the propeller, etc. up and down or left and right 360 degrees all around has the same structure as a rotating blade with a shroud that has a linear motor drive principle, and can be tilted with a wide range of angles. Use a rapid wind direction change device that can move quickly without any restrictions or limitations. At this time, the conventional rapid wind direction changing device was a disk shape or a cylindrical shape, but when a donut shape with a hollowed out central part was created and the outside of the donut shaped rapid wind direction changing device was fixed, The inner side turns and another quick wind direction change device is attached to the inner side so as to be orthogonal to create a biaxial quick wind direction change device. The inner quick wind direction change device has a double reversing shroud. It operates as a device for changing the direction of rapid air volume generation with a double reversing two-axis tilt that is integrated with a rotating blade.

  In order to control the aircraft as if it were an automobile running on the ground without manipulating complicated wings during maneuvering during level flight, it is necessary to change the blowing direction of propellers etc. quickly and accurately. It must be possible at any time and the thrust can be increased or decreased in a timely manner. The tilt device related to the fan engine of Patent Document 4 has a large gyro effect of the fan engine rotating at high speed, and the tilt speed of the two-pin rack and pinion cylinder device is slow and the tiltable angle range is limited. In addition, since the delicate change in the thrust of the fan engine is extremely difficult, the steering performance is not necessarily improved even with two axes. However, the double-reversed shroud rotor blade of the present invention can cancel out the strong gyro effect in the engine and can easily increase or decrease the rotational speed for changing the thrust without any time delay. In addition, the 2-axis tilt rapid wind direction changing device has no limit or limit in the tiltable angle range, the tilt is quick, and the setting of the blowing direction is digitally accurate. Therefore, since the rapid air volume generating wind direction changing device of the double reversing 2-axis tilt of the present invention can freely change the air volume and the blowing direction both vertically and horizontally, it can sufficiently contribute to the improvement of the steering performance. .

  At the time of cruising, a rapid air volume generating wind direction changing device with double reversing 2-axis tilt is used as a thrust device, and the wing lifts. However, in the case of short take-off and landing, when the speed of the airframe is reduced and sufficient wing lift cannot be obtained, or when the altitude of the airframe is subsidized when turning, the embodiment of FIGS. In the embodiment of FIGS. 21 to 28, the operation of the blow direction of the rapid air volume generation wind direction change device of the double reversing two-axis tilt is performed to give a depression angle, and a part of the thrust is used as the lift to assist the wing lift. The lift is assisted by increasing or decreasing the air volume of a rotating blade with a fixed large-diameter rotating duct type shroud that does not have a tilt device.

  A rotor blade with a shroud, which has a linear motor drive principle, is energy-saving and capable of generating large lift and thrust, and is lightweight. Since the present invention is a double-reversed rotor blade with shroud that cancels out the intense gyro effect generated by the shroud rotor blade, it can be attached to a fragile portion such as a blade tip of a fixed wing aircraft. is there. Further, unlike Patent Document 4, which has a problem in the angle restriction in the blowing direction of the air volume and the slow rotation speed even in the case of two axes, the rapid wind direction changing device of the two-axis tilt of the present invention blows out at 360 degrees all around. There are no restrictions or limitations on the direction, and any direction can be changed quickly and accurately, making it possible to substitute for the operation of the rudder's rudder. By using the double reversing two-axis tilt rapid air volume generating wind direction changing apparatus integrated with the wind direction changing apparatus, a vertical take-off and landing aircraft having high maneuverability can be created.

  As for the creation of the prime mover, the linear motor can be used because it is possible to pursue an energy-saving and efficient method, and when creating the double reversal, it can be realized with only an electrical device and does not require a complicated mechanism such as a gear device. A rotor blade with a shroud having the following driving principle is adopted. At this time, since the blowing direction is rapidly changed at the place of use, the rotating duct type shroud-equipped rotor blade described in Patent Document 1 having a structure that can cope with the rapid change in the blowing direction can cancel the gyro effect. Two are created in the direction of the vertical axis of rotation.

  Regarding the creation of the tilt mechanism, any of the electric motor, gear device, planetary gear device, and rack and pinion device is not sufficient in tilting speed. Further, the hydraulic device and the rack and pinion type cylinder device that can relatively increase the rotation speed have a limit in the tiltable angle. Therefore, the rapid wind direction changing device of Patent Document 2 that can be tilted at high speed and has no limitation on the tiltable angle is used. However, since the two-axis tilt mechanism cannot be created as it is, the central portion of the first rapid wind direction changing device installed horizontally is cut out in a donut shape, and the second quick wind direction changing device is cut inside the first rapid wind direction changing device. Similarly, a donut-shaped rapid wind direction changing device mounted perpendicularly perpendicularly is used as a two-axis tilt rapid wind direction changing device.

  The vertical take-off and landing aircraft generates lift during take-off and landing, the generation of thrust during cruising, and the creation of a device that performs the direction of the aircraft in place of the operation of the wing. The first and second donut-shaped rapid wind direction changing devices are combined so as to be orthogonal to each other, and are attached so as to be orthogonal to the inner peripheral portion of the second rapid wind direction changing device inside the two-axis tilt rapid wind direction changing device. By making it a single unit, and making this a double direction reversing two-axis tilt rapid air volume generating wind direction changing device, lift, thrust during cruising, and thrust during steering are obtained.

  In the present invention, a double air-reversing 2-axis tilt rapid air volume generating wind direction changing device, which serves as a lift force during take-off and landing, thrust during cruise, and thrust that serves as a rudder, is attached to the wing of the fuselage to form a vertical take-off and landing aircraft.

  1 to 4 show the implementation of a double-reversed rotor blade with a shroud in which two rotor blades with a rotating duct type shroud of Patent Document 1 are overlapped so as to reversely rotate so as to cancel out the powerful gyro effect. It is an example.

  5 to 8, the same second rapid wind direction changing device is attached so as to be orthogonal to the inside of the first rapid wind direction changing device in which the central portion of the rapid wind direction changing device of Patent Document 2 is cut out in a donut shape. In addition, it is an embodiment of a two-axis tilt rapid wind direction changing device.

  FIGS. 9 to 12 show an embodiment of a double-reversed twin-shaft rapid air volume generating wind direction changing device in which a rotating blade with a double-reversed shroud is attached to the inner periphery of the two-axis tilt rapid wind direction changing device. .

  FIGS. 13 to 20 show a vertical take-off and landing aircraft with a double reversing and biaxial tilt rapid air volume generating wind direction changing device with four units (one on four wings), one on each of the four wings of the fuselage. This is an example.

  FIGS. 21 to 28 show four sides of a double-reversed biaxial tilt rapid airflow generation wind direction change device on the wing of the fuselage, and a fixed large-diameter rotary duct type shroud rotary wing without a tilt device on one side of the fuselage. This is an example of a vertical take-off and landing aircraft in which a total of 8 units (4 units on each side) are attached on both sides.

  The prime mover of the vertical take-off and landing aircraft of the present invention is a rotor blade with a shroud having a driving principle of a linear motor capable of efficiently rotating a propeller or the like by applying an operating point of rotational force to the vicinity of the blade tip of the rotor blade. Compared to the case of a prime mover that applies a driving force for rotation to the central axis of rotation, much energy saving can be realized. Also, a rotor blade with a shroud that has a linear motor drive principle is more effective in generating lift and thrust the larger its diameter, so it can be used for mass transport by creating a large vertical takeoff and landing. Easy. Even in the case of making a large aircraft, the combination of the double reversing two-shaft tilt rapid air volume generating wind direction changing device of the present invention and the fixed large-diameter rotating duct type shroud-equipped rotor blade without the tilt mechanism. Can reduce the height of the fuselage even when using a rotor blade with a large-diameter rotating duct type shroud, which can reduce the resistance to the direction of travel and increase the transport capacity and speed of the vertical take-off and landing aircraft. Can be realized at the same time. In addition, since there is no choice of takeoff and landing locations, it is possible to use poorly equipped airfields or places such as plazas in case of emergency. Furthermore, the double-reversing 2-axis tilt rapid air volume generating wind direction changing device is very responsive to both increasing and decreasing the air volume and changing the wind direction. By changing the air volume and direction of the changing device, it is possible to easily control the vehicle as if it were running on the ground, so the burden on the operator can be reduced.

  It is a front view of a rotary blade with a shroud of double reversal.   It is a top view of a rotating blade with a shroud of double reversal.   It is a side view of a rotating blade with a shroud of double reversal. An alternate long and short dash line indicates a portion to be cut and displayed, and a tail arrow indicates the direction of viewing the cut surface.   It is sectional drawing of a rotary blade with a double reversal shroud.   It is a front view of the rapid wind direction change apparatus of a biaxial tilt.   It is a top view of the rapid wind direction change apparatus of a biaxial tilt.   It is a side view of the rapid wind direction change apparatus of a biaxial tilt. An alternate long and short dash line indicates a portion to be cut and displayed, and a tail arrow indicates the direction of viewing the cut surface.   It is sectional drawing of the rapid wind direction change apparatus of a biaxial tilt.   It is a front view of the rapid air volume generation | occurrence | production direction change apparatus of a double inversion 2 axis tilt.   It is a top view of the rapid air volume generation | occurrence | production direction change apparatus of a double inversion 2 axis tilt.   It is a side view of the rapid air volume generation | occurrence | production direction change apparatus of a double inversion 2 axis tilt. An alternate long and short dash line indicates a portion to be cut and displayed, and a tail arrow indicates the direction of viewing the cut surface.   It is sectional drawing of the rapid air volume generation | occurrence | production direction change apparatus of a double inversion 2 axis tilt.   It is a front view at the time of take-off and landing of a vertical take-off and landing aircraft in which four rapid air volume generation wind direction changing devices with double reversing two-axis tilt are attached to the wings of the fuselage.   It is a top view at the time of take-off and landing of a vertical take-off and landing aircraft in which four double reversing two-axis tilt rapid air volume generation wind direction changing devices are attached to the wings of the fuselage.   It is a side view at the time of take-off and landing of a vertical take-off and landing aircraft in which four double-reversing two-axis tilt rapid air volume generation wind direction changing devices are attached to the wings of the fuselage.   It is the top view at the time of the horizontal flight of the vertical take-off and landing aircraft which attached the rapid air volume generation | occurrence | production direction change apparatus of a double inversion 2 axis tilt to the wing | blade of the body.   Swing the blowing direction of the previous two double-reversing 2-axis tilt rapid airflow generating wind direction changing devices of the vertical take-off and landing aircraft with four double-reversing 2-axis tilt rapid airflow generating wind direction changing devices attached to the wings of the fuselage It is a top view in the case of turning the body to the right direction. The direction of travel of the aircraft can be controlled only by the thrust of the double reversing and biaxial tilt rapid air volume generating wind direction changing device, so that the wings are not tilted and horizontal flight can be maintained even during the direction change.   Swing the blowing direction of the front and rear four double-reversed 2-axis tilt rapid airflow generation wind direction changers of the vertical take-off and landing aircraft with four double-reversed 2-axis tilt rapid airflow generation direction change devices attached to the wings of the fuselage. It is a top view at the time of translating slowly to the right direction by a thing. Lateral translation, which was not possible with conventional aircraft (except for Control Configurable Vehicle (CCV)), can be performed only with the thrust of the double-reversed 2-axis tilt rapid wind generation device. .   Swing the blowing direction of the front and rear four double-reversed 2-axis tilt rapid airflow generation wind direction changers of the vertical take-off and landing aircraft with four double-reversed 2-axis tilt rapid airflow generation direction change devices attached to the wings of the fuselage. It is a top view in the case of translating the airframe rapidly to the right by this. This is an abrupt side-to-side translation that has not been possible with conventional aircraft (including the Control Configurated Vehicle (CCV)), but the vertical take-off and landing aircraft of the present invention does this during cruising. Used for special cases such as avoiding sudden obstacles or dodging missile tracking on the battlefield.   Blowing direction of the front / rear two-inverted 2-axis tilt rapid air volume generating wind direction changer for the vertical take-off and landing aircraft with four double-reversing 2-axis tilt rapid air volume generating wind direction changing apparatuses attached to the wings of the fuselage FIG. 6 is a plan view when the aircraft is suddenly turned to the right by swinging in the opposite directions. It is a kind of spin flight like aerobatics, but it can be implemented only by thrust operation of the wind direction change device with double reversing 2-axis tilt, so this book can be used while the speed of the vertical take-off and landing aircraft remains sufficiently It is not a difficult maneuver for the inventive vertical take-off and landing aircraft.   There are 4 double-rotating 2-axis tilt rapid airflow generating wind direction changing devices on the wings of the aircraft, 4 fixed large-diameter rotary duct type shroud rotary wings without a tilt device on the side of the aircraft, 8 in total It is a front view at the time of takeoff and landing of the installed vertical takeoff and landing aircraft.   There are 4 double-rotating 2-axis tilt rapid airflow generating wind direction changing devices on the wings of the aircraft, 4 fixed large-diameter rotary duct type shroud rotary wings without a tilt device on the side of the aircraft, 8 in total It is a top view at the time of the take-off and landing of the attached vertical take-off and landing aircraft.   There are 4 double-rotating 2-axis tilt rapid airflow generating wind direction changing devices on the wings of the aircraft, 4 fixed large-diameter rotary duct type shroud rotary wings without a tilt device on the side of the aircraft, 8 in total It is a side view at the time of the take-off and landing of the attached vertical take-off and landing aircraft.   There are 4 double-rotating 2-axis tilt rapid airflow generating wind direction changing devices on the wings of the aircraft, 4 fixed large-diameter rotary duct type shroud rotary wings without a tilt device on the side of the aircraft, 8 in total It is a top view at the time of the horizontal flight of the attached vertical take-off and landing aircraft.   There are 4 double-rotating 2-axis tilt rapid airflow generating wind direction changing devices on the wings of the aircraft, 4 fixed large-diameter rotary duct type shroud rotary wings without a tilt device on the side of the aircraft, 8 in total It is a top view in case the attached vertical take-off and landing aircraft swings to the right while swinging the blowing direction of the wind direction changing device of the two forward-reversing two-axis tilting rapid air volume generating devices. In this case, the fixed large-diameter rotating duct type shroud-equipped rotor blade having no tilt device can always generate the necessary lift, so that it can be turned regardless of the presence or absence of the speed of the airframe. In addition, by turning the lift of the rotor blade with a large-diameter rotating duct type shroud on the inside and outside of the turn, the direction of turning can be changed while maintaining the level of the aircraft like a four-wheeled vehicle. It is possible to change the direction of the body tilted like a wheel bike or to act like a slalom.   There are 4 double-rotating 2-axis tilt rapid airflow generating wind direction changing devices on the wings of the aircraft, 4 fixed large-diameter rotary duct type shroud rotary wings without a tilt device on the side of the aircraft, 8 in total It is a top view in case the attached vertical take-off and landing aircraft slowly translates the aircraft in the right direction by swinging the blowing direction of the front and rear four double reversing two-axis tilt rapid air volume generation wind direction changing devices. Transverse movement that was not possible with conventional aircraft (excluding Control Configurated Vehicle (CCV)) was carried out only by thrust operation of the wind direction change device with double-reversed 2-axis tilt rapid air flow generation it can. In this case, a fixed large-diameter rotary duct type rotor blade with a shroud that does not have a tilt device can always generate the necessary lift, and can therefore be implemented regardless of the presence or absence of the airframe.   There are 4 double-rotating 2-axis tilt rapid airflow generating wind direction changing devices on the wings of the aircraft, 4 fixed large-diameter rotary duct type shroud rotary wings without a tilt device on the side of the aircraft, 8 in total It is a top view in case the attached vertical take-off and landing aircraft moves the airframe rapidly in the right direction by swinging the blowing direction of the front and rear four double reversing two-axis tilt rapid air volume generation wind direction changing devices. This is an abrupt side-to-side translation that has not been possible with conventional aircraft (including the Control Configurated Vehicle (CCV)), but the vertical take-off and landing aircraft of the present invention does this during cruising. Used for special cases such as avoiding sudden obstacles or dodging missile tracking on the battlefield. In this case, a fixed large-diameter rotary duct type rotor blade with a shroud that does not have a tilt device can always generate the necessary lift, and can therefore be implemented regardless of the presence or absence of the airframe.   There are 4 double-rotating 2-axis tilt rapid airflow generating wind direction changing devices on the wings of the aircraft, 4 fixed large-diameter rotary duct type shroud rotary wings without a tilt device on the side of the aircraft, 8 in total The installed vertical take-off and landing aircraft are opposite to each other in the blowing direction of the two airflow direction change devices for the double reversing two-axis tilt and the two airflow direction change devices for the rear two double reversing two-axis tilt. It is a top view in the case of swinging right and rapidly turning right. In this case, the fixed large-diameter rotary duct type shroud-equipped rotor blade having no tilt device can generate lift at all times, so that it can be turned regardless of whether the airframe is present or not.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 Double reversing rotor blade with shroud 2 1st rapid wind direction change device 3 2nd rapid wind direction change device 4 Double direction 2 axis tilt rapid air volume generation wind direction change device 5 Fixed large diameter without tilt device Rotating duct type rotor blade with shroud 6 Air flow direction (wake direction) produced by the rapid air flow generating device
11 shroud 12 blade 13 hub 101 electromagnet 102 permanent magnet 103 rotating duct

Claims (4)

  It is characterized by offsetting the powerful gyro effect that occurs in the case of a single unit by creating a rotating blade with shroud that has the driving principle of two linear motors rotating in reverse to each other in the direction of the vertical axis of rotation. A rotating blade with a double reversing shroud.   Attach a second similar rapid air direction change device so as to be orthogonal to the inner rotating inner periphery of the first rapid air direction change device having a linear motor driving principle, which is hollowed out in a donut shape. If one inner peripheral portion is rotated 360 degrees around the horizontal axis, the other inner peripheral portion is rotated 360 degrees around the vertical axis, so that the inner peripheral portion of the second rapid wind direction changing device is entirely A two-axis tilt rapid wind direction change device characterized by enabling quick, accurate and free movement with respect to the circumference.   The rotating blade with double reversing shroud according to claim 1 is integrally mounted so as to be orthogonal to the inner peripheral portion of the second rapid wind direction changing device constituting the rapid wind direction changing device of the biaxial tilt according to claim 2. Thus, the air flow can be generated and changed freely, and the wind direction can be changed quickly and accurately over the entire circumference.   The airflow direction change device for the double reversing 2-axis tilt is installed on the wing of the fuselage, and the airflow and direction of the airflow change device for the double reversing 2-axis tilt can be changed instead of operating the wing. A vertical take-off and landing aircraft, which can be operated by changing to

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