JP4441714B2 - Multi-axis vertical take-off and landing aircraft - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a multi-axis vertical take-off and landing aircraft that can simultaneously rotate a plurality of variable pitch rotary blades from a single power transmission rotary shaft.
[0002]
[Prior art]
Conventionally, a large number of bevel gears have been used to attach a plurality of driven rotating shafts to a single power transmission shaft.
[0003]
[Problems to be solved by the invention]
In order to perform the same function as that of the present invention with the prior art, it was necessary to use a large number of bevel gears as shown in FIG. The reason for this is that a large number of bevel gears are used when functions such as the distance from the power transmission rotating shaft to the driven rotating shaft, the axial direction of the driven rotating shaft, the rotating direction, the rotational speed, and the counter torque cancellation of the driven rotating shafts are incorporated. Will do. In addition, a large number of components such as a bearing that supports the bevel gear and a rotating shaft that transmits rotation to the bevel gear are necessary, and the number of components as a whole that support these components is too large and structurally complicated. Therefore, there are many problems such as cost increase, weight increase, processing, and assembly accuracy, and the reliability is very inferior when used for a multi-axis vertical take-off and landing aircraft. Further, in the case of a conventional multi-axis type vertical take-off and landing aircraft, there is a problem that the distance between the rotary shafts becomes long and the body becomes large if the respective rotor rotation radii do not overlap. On the other hand, in the case of an arrangement in which the rotation radii of the respective rotors overlap, particularly when the rotor 4 axes having two rotor blades are arranged at positions intersecting each other, interference between the rotor blades becomes a problem. End up. The present invention has been made to solve the above-described problems.
[0004]
[Means for Solving the Problems]
In order to solve the above problems, in the multi-axis vertical take-off and landing aircraft according to the present invention, one engine and a single power transmission shaft extending from the engine are respectively arranged at the vertex positions of a rectangular frame, A multi-axis vertical take-off and landing aircraft in which rotors 4 shafts each having two variable pitch rotors are connected by a gear unit comprising a screw gear (5) and a screw gear (6), The front and rear two left and right axes are arranged at positions where the rotor blades intersect each other, and the front two-axis and rear two-axis rotors are arranged so that the rotor blades do not intersect, and in order to protect the rotor blades It is equipped with a rotary blade protective device arranged around all the rotary blade rotation ranges.
[0005]
[Action]
In the multi-axis vertical take-off and landing aircraft according to the present invention, the left and right two-axis rotors are arranged at positions where the rotor blades intersect each other, and the front and rear rotors are arranged so that the rotation radii do not overlap. It is possible to prevent interference between the rotor blades and to reduce the size of the airframe. In addition, this gear unit structure increases the degree of freedom in setting the screw gear shaft in the take-out direction, increases the degree of freedom in setting the high-speed rotation, and counteracts the counter-torque because the screw gear shafts reverse each other. It is a possible gear mechanism. Therefore, the number of components is reduced and the structure becomes simple, and the advantages such as cost reduction and weight loss increase.
[0006]
DETAILED DESCRIPTION OF THE INVENTION
Examples of the present invention will be described below.
[0007]
[First Embodiment]
As shown in FIGS. 5 and 7, the screw gear (6) is assembled at an angle so as to mesh with both sides of the screw gear (5). A right front rotor (FR) and a left front rotor (FL) having two variable pitch rotor blades (17) are disposed at the other end of the screw gear . These rotors are provided with a servo (9), and the pitch angle of each rotor blade (17) can be changed by its operation. As shown in FIG. 2, these gear units (F) and gear units (R) are arranged in the front-rear direction and connected by a connector (2). Further, the gear unit (F) and the screw gear (5) of the gear unit (R) are connected by the power transmission rotating shaft (1). The connector (2) is provided with an engine (18) for rotating the power transmission rotary shaft (1) through a reduction gear (19) for rotation output. The basic overall structure of the multi-axis type vertical take-off and landing aircraft according to the present invention is as described above, and the right front rotor (FR), the left front rotor (FL), and the right rear rotor (RR ) with one power transmission shaft (1). ) And the left rear rotor (RL) are rotated simultaneously.
[0008]
More specifically, the screw gear (5) is assembled to the bearings (8) fixed to the two frame plates (7), and the screw gear (6) is engaged with both sides of the screw gear (5). Is assembled to the frame plate (7) through the screw gear shaft holder (4) at an angle as shown in FIG. At this time, the arrangement of the rotor blades (17) is shifted by 90 degrees so that the right front rotor (FR) and the left front rotor (FL) provided at the other end of the shaft of the screw gear (6) do not contact each other. deep. The rotor blades (17) of the right front rotor (FR) and the left front rotor (FL) are servo-linked by the operation of each servo (9) attached to the frame plate (7) via the servo holder (22). (10) The pitch angle can be changed via the L link (11), the operating rod (12), the pitch control head (13), the pitch adjustment link (14), and the rotary blade holder (15).
[0009]
The gear mechanism having the above structure and function is used as one gear unit, and the front side of this gear unit is (R) and the rear side is (R). . The screw gears (5) of the gear units (F) and (R) are connected by the power transmission rotating shaft (1). The power transmission rotating shaft (1) also has a role of canceling out the thrust load generated by the characteristics of the screw gear. Therefore, the tooth trace directions of the gear units (F) and (R) are opposite to each other, and the thrust loads of the gear units (F) and (R) cancel each other as the power transmission rotating shaft (1) is attracted to each other. . An engine (18) is attached to the connector (2), and the power transmission rotating shaft (1) is rotated via a reduction gear (19). In addition, a box (20) containing a fuel tank and electrical components, and a leg (21) are attached.
[0010]
When the present invention is used in the structure as described above, it is connected by increasing the rotational output of the engine (18) and rotating the power transmission rotating shaft (1) via the reduction gear (19). The screw gear (5) of the gear unit (F) and the gear unit (R) is rotated. As a result, the right front rotor (FR), the left front rotor (FL), the right rear rotor (RR), and the left rear rotor (RL) are all rotated simultaneously, generating lift and starting to rise. The pitch angle of each rotor blade of the right front rotor (FR), left front rotor (FL), right rear rotor (RR) and left rear rotor (RL) is raised, lowered, and airborne by operating each servo (9). It can take actions of stationary, back and forth movement, left and right movement, and turning.
[0011]
For example, in order to move forward, if the operation of lowering the pitch angle of each rotor blade of the right front rotor (FR) and left front rotor (FL) in FIG. 1 is performed, the lift is reduced and the nose is lowered. At the same time, if the pitch angle of the rotor blades of the right rear rotor (RR) and the left rear rotor (RL) is increased, the lift increases and the heel is lifted up to move forward and move forward. If this operation is reversed, it will be in a backward tilted posture and can be moved backward. Similarly, for the left-right movement, the pitch angle of each rotor blade of the right two-axis rotor and the left two-axis rotor may be manipulated. As described above, it is possible to fly by controlling the attitude of the aircraft simply by manipulating the pitch angle. Furthermore, it is possible to quickly cope with large center of gravity fluctuations caused by the lifting and lowering of a person by raising and lowering the load at the position of the center of gravity of the fuselage and the position outside the rotor shaft as shown in FIG.
[0012]
[Second Embodiment]
The gear unit (F) and the gear unit (R) of the first embodiment are arranged at the front and rear, and are connected by an angled connector (2a) as shown in FIG. Accordingly, the front gear unit (F) is inclined forward with respect to the horizontal plane, and the right front rotor (FR) and the left front rotor (FL) are also inclined forward. The rear gear unit (R) is tilted backward, and the right rear rotor (RR) and the left rear rotor (RL) are tilted backward. Since the right and left rotors (FR) and the right rear rotor (RR) are mounted on the right and left sides of the gear unit (F) and the gear unit (R) at an angle so as to incline toward each other. The left front rotor (FL) and the left rear rotor (RL) are inclined in the left outer direction. As described above, since the angle is provided in the front-rear direction, a universal joint (23) is provided on the power transmission rotating shaft (1a) for transmitting rotational power to the screw gear (5) of the gear unit (F) and the gear unit (R). , It is connected so that it can be rotated even at an angle. The angled coupler (2a) is provided with an engine (18), and a power transmission rotating shaft (1a) with a universal joint (23) is rotated via a reduction gear (19). In addition, a box (20) containing a fuel tank and electrical components, and a leg (21) are attached.
[0013]
The second embodiment is structured as described above. When this is used, the rotational output of the engine (18) is increased, and the power transmission rotary shaft (1a) with a universal joint (23) is provided via the reduction gear (19). ) To rotate the connected front and rear screw gears (5). As a result, the right front rotor (FR), left front rotor (FL), right rear rotor (RR), and left rear rotor (RL) with various inclinations are all rotated simultaneously, generating lift and starting to rise. By operating the pitch angle of each rotor blade of the right front rotor (FR), left front rotor (FL), right rear rotor (RR) and left rear rotor (RL) with each servo (9), the machine body is not tilted. In addition, it can move up, down, stand still in the air, move back and forth, move left and right, and turn.
[0014]
For example, if the pitch angle of each rotor blade of the right front rotor (FR) and the left front rotor (FL) is increased to move forward, the lift increases and the gear unit (F) tilts forward. Be drawn to the front. If this operation is reversed, it can move backward. Similarly, in the case of left-right movement, if the pitch angle of each rotor blade of the right two-axis rotor or the left two-axis rotor is manipulated , the aircraft can move and fly without tilting the aircraft.
[0015]
[Third Embodiment]
As shown in FIG. 9 , all the rotating blade rotations of the right front rotor (FR), the left front rotor (FL), the right rear rotor (RR), and the left rear rotor (RL) as shown in FIG. Around the range, equipped with a protector (25) so that the rotor blades do not touch the obstacles and are destroyed, connect the connector (2) from the rotation range of the right front rotor (FR) and the left front rotor (FL). also installed an extended hatch to the front (24). The third embodiment has the structure as described above, and in order to use this, the engine (18) is rotated and lifted in the air, approaching a high-rise building (26) from the front, Or it can be made to lie directly to the window (27), and the luggage can be lifted and lowered from the elevator opening (24), and people can get on and off. At this time, the airframe becomes unstable due to large fluctuations in the center of gravity. Therefore, it is necessary to instantaneously manipulate the pitch angle of the variable pitch rotor blade. For example, the moment the cargo is unloaded, the front of the aircraft becomes lighter and floats up, and the aircraft as a whole is tilted backward. At this moment, the pitch angle of the rotor blades of the right front rotor (FR) and the left front rotor (FL) is lowered and the pitch angle of the rotor blades of the right rear rotor (RR) and the left rear rotor (RL) is increased to perform horizontal operation. The posture can be maintained.
[0016]
【The invention's effect】
As is clear from the description of the above embodiment, in the multi-axis vertical take-off and landing aircraft according to the present invention , the rotor rotor blades of the left and right axes are arranged at positions where they intersect each other, and the rotation radii between the front and rear rotors do not overlap. Therefore, it is possible to prevent the front and rear rotor blades from interfering with each other and to reduce the size of the airframe. In addition, since each of the four-axis rotors can be individually operated, even if there is a change in the center of gravity on the aircraft, the influence can be canceled instantaneously and a stable flight can be maintained. Furthermore, the multi-axis type vertical take-off and landing aircraft of the present invention can be simultaneously rotated by a simple combination of a single reactor power transmission rotating shaft and a screw gear, and further, with a simple lower pitch rotating blade. A multi-axis vertical take-off and landing aircraft that can be combined. In an aircraft, a simple mechanism is ideal, and being able to approach or directly lay on a high-rise building or the like expands the field of activity more than ever. As an example, it can be performed from the air, such as quick fire extinguishing activities and rescue activities in the event of a high-rise building fire.
[0017]
[Brief description of the drawings]
FIG. 1 is a plan view of the present invention, FIG. 2 is a side view of the present invention, FIG. 3 is a front view of the present invention, and FIG. 4 is a plan view of the gear unit of the present invention. Is omitted.
FIG. 5 is a front view of the gear unit of the present invention, and a part of the rotor blade is omitted for convenience of explanation.
FIG. 6 is a side view of the gear unit of the present invention, and a part of the rotor blade is omitted for convenience of explanation.
7 is a simplified reference perspective view of the gear unit of the present invention. FIG. 8 is a side view of the present invention. FIG. 9 is a perspective view of the present invention. ]
[Explanation of symbols]
F-front gear unit R-rear gear unit FR- right front rotor FL- left front rotor RR- right rear rotor RL- left rear rotor 1-power transmission rotary shaft 1a-power transmission rotary shaft 2 with universal joint Connector 2a-Angled connector 3-Connector fixing band 4-Screw gear shaft holder 5-Screw gear 6-Screw gear 7-Frame plate 8-Bearing 9-Servo 10-Servo link 11-L link 12-Operation Rod 13-Pitch control head 14- Pitch adjustment link 15-Rotating blade holder 16- Right rotating blade 17- Left rotating blade 18-Engine 19-Reduction gear 20-Storage box 21-Leg 22-Servo holder 23-Free joint 24-Elevator 25-Rotary blade protector 26-High-rise building 27-High-rise building window

Claims (1)

A rotor 4 shaft that includes one engine and is arranged at the apex position of a rectangular frame with respect to a single power transmission rotating shaft extending from the engine, each having two variable pitch rotating blades, A multi-axis vertical take-off and landing aircraft connected respectively by a gear unit comprising a screw gear (5) and a screw gear (6) , wherein the rotor blades intersect each other on the left and right two axes of the front and rear of the rotor. The rotors of the front 2-axis and the rear 2-axis are arranged so that the rotor blades do not cross each other, and the rotor blade protection arranged around all the rotor blade rotation ranges to protect the rotor blades. Multi-axis vertical take-off and landing aircraft characterized by the equipment.

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