JP2014169064A - Disc lift type flying body (close type) - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide "a vertical take-off and landing plane based on new fluid mechanics principles" that achieves "improving defects such as causing wind pressure damage in the periphery and generating remarkable noise in the takeoff and landing like a helicopter" and "enabling upsizing of a machine body being impossible in the helicopter and enabling high-speed flight".SOLUTION: A vertical landing or taking-off flight principle is provided by floating a machine body using lift generated in an upper surface of a high-speed rotating disc 1 in the upper part of a main body of a machine body. "The ascent and descent in the vertical direction and the movement of an aerial stop, therefore the vertical landing or taking-off motion" are freely enabled by adjusting "the magnitude of the rotational speed of a rotating disc, namely the strength and weakness of the lift acting toward the upper part of the machine body". Also, the machine body is enlarged by making the number of discs more than one, and a high-speed flight is enabled by making the contour of the whole machine body into a smooth and streamlined shape without projecting or foreign matter.

Description

The present invention
1. Its main structure is
A rotating disk 1 which is located above the body body 2 and rotates with the “rotary shaft 3 held by the bearing member 9 in the body body 2” as a rotation axis.
B. A rotating shaft 3 having a rotational axis centered on the center of the rotating disk 1 is held by the bearing member 9 and is “this rotating shaft 3 for rotating the rotating disk 1”. A motor 4 that gives a rotational force to the shaft or a turbine mechanism that gives a rotational force to the rotary shaft 3 using a high-speed air flow or a human-powered mechanism that gives a rotational force to the rotary shaft 3 using a leg arm force or the like is installed. Airframe body 2.
Composed of two kinds of members
2. “Smoothly-formed bottom surface 6 of rotating disk 1” and “the bottom surface 6 of this rotating disk 1 have substantially the same diameter, and are installed on the bottom surface 6 of this rotating disk 1 in the nearest opposite plane and By setting the gap between the upper and lower surfaces of the smoothly formed “smooth circular surface 7 of the upper surface of the fuselage body 2” “to be extremely narrow so that both the upper and lower surfaces do not contact”
Or, by “sealing the gap between the upper and lower surfaces and setting the space as this gap to a vacuum state / very low pressure air state”,
Or "by sealing the gap between the upper and lower surfaces and enclosing a low specific gravity gas such as hydrogen gas, helium gas or hot air in the space as this gap"
3. “The upper surface of the space as the gap between the upper and lower surfaces, that is, the lower surface 6 of the rotating disk 1 and the lower surface of the space as the gap between the upper and lower surfaces, that is, the lower surface of the machine body 2, generated by rotating the rotating disk 1 at high speed. Making each of the atmospheric pressures as kinetic fluid pressures generated and acting on both surfaces of the smooth circular surface 7 of the upper surface equal or sufficiently approximate,
4. Thus, “actually generated on the upper surface 5 of the rotating rotating disk 1 and acting on the lower surface 8 of the airframe body 2 and“ atmospheric pressure as a kinetic fluid pressure generated due to a difference in motion speed from the stationary atmosphere ”. `` Relative pressure difference between both atmospheric pressures of atmospheric pressure as static fluid pressure due to atmospheric pressure '', that is, `` pressure difference generated when the former atmospheric pressure is relatively low and the latter atmospheric pressure is relatively high ”Is used as“ lifting force ”and the“ whole body composed of the rotating disk 1 and the airframe body 2 ”is levitated upward,
5. By adjusting “the magnitude of the rotational speed of the rotating disk 1 generated by the adjustment operation of the rotational speed of the prime mover 4, that is, the strength of the lift acting toward the upper part of the aircraft”, the “rising and descending in the vertical direction and the air It is a “disk lift type air vehicle” characterized in that it can freely perform a stop motion and thus a vertical take-off and landing motion.

The “pile that can be used for vertical take-off and landing” currently in practical use is roughly divided into
1. A helicopter that gains ascending force by rotating the rotor at the top of the aircraft.
2. Jet aircraft mainly jet aircraft that jets jet gas downwards and gains upward force as a reaction.
3. A flying body that produces a descending airflow by rotating one or more propellers or ducted fans to obtain ascending force.
There are three types of

As in the present invention, that is, as in “a disk lift type flying body described in“ Claim 1 ”and“ Technical Field ”above”,
(B) “The bottom surface of the rotating disk that is formed smoothly” and “The bottom surface of this rotating disk is almost the same diameter, and is placed on the bottom surface of this rotating disk in the immediate opposite plane and is formed smoothly. By setting the gap between the upper and lower surfaces of the machine body to the “smooth circular surface on the upper surface” is set so narrow that the upper and lower surfaces are not in contact with each other.
B) Generated by rotating the rotating disk at a high speed `` both the upper surface of the space as the gap between the upper and lower surfaces, that is, the lower surface of the rotating disk, and the lower surface of the space as the gap between the upper and lower surfaces, that is, the smooth circular surface of the upper surface of the main body. `` Each atmospheric pressure as kinetic fluid pressure generated and acting on each surface '' is made identical or sufficiently approximated,
C) Rotating the rotating disk at the top of the fuselage at high speed, `` The atmospheric pressure as the operating fluid pressure generated and acting on the upper surface of the rotating rotating disk '' and the `` static fluid pressure due to the atmospheric pressure acting on the lower surface of the fuselage body `` Relative pressure difference between both pressures '' of `` the pressure of the air '', i.e., `` pressure difference generated when the former pressure is relatively low and the latter pressure is relatively high '' is used as `` lift ''. “Aircraft that can move freely in vertical takeoff and landing” using the “hydrodynamic principle” that levitates the “whole body composed of a rotating disk and the body”.
Since there seems to have never existed in principle and actual machine, there seems to be no related literature.

At present, the three types of aircraft described above have been put into practical use as “aircraft capable of vertical take-off and landing”, but all of these aircraft are “rotor jet engine propellers and ducted fans”. It is used to generate a powerful downdraft and use the reaction to lift the aircraft.
For this reason, any aircraft
1. When taking off and landing, there was a defect that wind pressure was blown away from the bottom of the fuselage and the surroundings were blown away or dust was blown up.
2. During take-off and landing, as well as low-flying flights, there were drawbacks such as “pattering sound due to rotor rotation”, “jet jet sound consisting of high-frequency sound” and “rotating sound of propeller and fan”.
3. In the helicopters that occupy the overwhelming majority of practical aircraft, it is difficult to increase the size of the helicopter due to restrictions on the strength of the rotor. “Large capacity with a capacity of about 100 passengers and more than about several tens tons of cargo There was a drawback that the "airframe" could not be obtained.
4. In addition, there was a drawback that “high-speed flight exceeding 400 km / h” was not possible because the air resistance received by the rotor during forward flight was high.

The present invention refers to "a vertical takeoff and landing vehicle without the above drawbacks", i.e.
1. Vertical take-off and landing aircraft that does not cause wind pressure damage around the aircraft during take-off and landing.
2. Vertical take-off and landing aircraft that does not generate significant noise during low altitude flight as well as during take-off and landing.
3. A large vertical takeoff and landing vehicle with a capacity of about 100 crew members and a cargo capacity of several tens of tons or more.
4. A vertical take-off and landing vehicle capable of high-speed flight at a speed of about 500 km / h or higher.
The problem is to put this into practical use.

  As shown in FIGS. 1, 2, and 3, the present invention is a vertical structure that includes “rotary disk 1, main body 2, rotating shaft 3, prime mover 4, and bearing member 9” as main components. It is a take-off and landing vehicle, and the description regarding each component is as follows.

The description regarding “Rotating disk 1” is as follows.
1. It is installed in the upper part of the fuselage body 2 and has a “disc shape”.
2. It is fixed to “the upper part of the rotary shaft 3 having a rotational axis that coincides with the center of the disk” and “the lower part of the rotary shaft 3 is rotatably held by the bearing member 9”, thereby “the bearing member 9 and It is connected to the fuselage main body 2 ".
3. “The upper surface 5” is formed into a flat surface shape that is entirely smooth, or a conical shape, a spherical shape, or an arc shape with a raised central portion, and is exposed to the atmosphere.
4. “The lower surface 6” is formed into a smooth planar shape as a whole, and “the smooth circular surface 7 made of a smooth circular planar shape on the upper surface of the airframe body 2” is very narrow so that both planes do not come into contact with each other. Facing each other across a gap ”.
5. “The plane of the lower surface 6” is orthogonal to the rotational axis of the rotational shaft 3.

The description regarding “airframe body 2” is as follows.
1. “Rotating disk 1” is installed at the top.
2. The lower part of the “rotating shaft 3 whose upper end is fixed to the rotating disk 1 and has a rotation axis that coincides with the center of the disk” is rotatably held by the “bearing member 9 fixed to the airframe”.
3. Installed in the interior is “a prime mover 4 or a turbine mechanism or a human power mechanism for rotating the rotating shaft 3”.
4. Regarding the “positional relationship with the rotating disk 1”, the lower surface of the “smoothly formed lower surface 6 of the rotating disk 1” has substantially the same diameter as the lower surface 6 of the rotating disk 1. A “smooth circular surface 7 consisting of a smooth circular flat surface set on the upper surface of the airframe body 2” is installed on the lower surface 6 in parallel with the nearest opposing surface and is smooth.
5. “The distance between the planes of the lower surface 6 of the rotating disk 1 and the smooth circular surface 7 both of which are both formed smoothly and installed in parallel in the nearest opposite plane” is “both when the rotating disk 1 rotates. It is set narrowly until it becomes “a value very close to the minimum limit value that does not touch”.
6. “Plane of smooth circular surface 7” is orthogonal to the rotation axis of rotation shaft 3.

The description regarding the “rotary shaft 3” is as follows.
1. The upper end is fixed to “the center of rotation of the rotating disk 1”.
2. The lower end thereof is rotatably held by “the bearing member 9 fixed to the body 2”.
3. The rotational axis coincides with the center of the rotating disk 1 and is orthogonal to the “plane of the lower surface 6 of the rotating disk 1” and the “plane of the smooth circular surface 7 of the upper surface of the machine body 2”.
4. The shaft rotation is driven by the “motor 4 or turbine mechanism or manpower mechanism”.

The explanation about “Motor 4” is as follows.
1. It is fixed to the body 2.
2. It is directly connected to the rotary shaft 3 or indirectly via a rotation transmission member.
3. Generate “rotational motion as a prime mover” and perform “action to give axial rotation force to the rotary shaft 3”.
4. As a form of prime mover,
B) “Rotary force generating mechanism such as turbo-bloom engine, piston engine, electric motor” is connected directly to the rotating shaft 3 or indirectly through a rotation transmitting member, and the rotating shaft 3 is connected by the generated rotating force. A mechanism to rotate.
Or “turbine blades fixed to the rotating shaft 3 or turbine blades fixed to the rotating disk 1” or “turbine that applies rotational force to the rotating shaft 3 via the rotation transmission member connected to the rotating shaft 3”. A mechanism that rotates the rotating shaft 3 and the rotating disk 1 by applying a “high-speed air flow generated by using a jet engine, a turbo flop engine / piston engine, and a propeller / fan associated therewith”.
C, or “a human power mechanism that applies a rotational force to the rotating shaft 3 directly or indirectly through a rotation transmitting member using leg strength, arm force, or the like”.

The description regarding the “bearing member 9” is as follows.
1. It is fixed to the body 2.
2. “Rotating shaft 3 fixed to the center of rotation of rotating disk 1 on the upper side and connected to motor 4 on the lower side” is rotatably held.

  The “hydrodynamic principle in which lift is generated in the entire airframe by the rotation of the rotating disk 1” that makes the present invention will be explained according to “FIG. 4” and “FIG. 5” as schematic diagrams. is there.

In "Figure 4" and "Figure 5" as schematic diagrams,
Reference numerals 1 and 11 denote one point on the “upper surface 5 of the rotating disk 1” that “the eccentric distance from the rotational axis is r”.
Reference numerals 2 and 12 indicate one point on the “lower surface 6 of the rotating disk 1” that “the eccentric distance from the rotation axis is r”.
Reference numerals 3 and 13 indicate one point that “the eccentric distance from the rotation axis r is” on the “smooth circular surface 7 of the main body 2”.
Reference numerals 4 and 14 denote one point where “the eccentric distance from the rotation axis r is” on the “lower surface 8 of the main body 2”.
And
5, “Atmospheric pressure acting on the upper surface 5 of the rotating disk 1 at the point 11” Pa.
6, “Atmospheric pressure acting on the lower surface 6 of the rotating disk 1 at the point 12” Pb.
7, “Atmospheric pressure acting on smooth circular surface 7 of airframe body 2 at point 13” Pc.
8. Pd is “atmospheric pressure acting on the lower surface 8 of the body 2 at the point 14”.
9. “Atmospheric pressure around the aircraft” Pe.
If
Further, if “the main body 2 does not rotate about the rotation axis 3 and the rotation disk 1 can rotate at any rotation speed about the rotation axis 3”. If

In “FIG. 4” as a “schematic diagram when the upper rotating disk 1 and the lower machine body 2 connected by the rotating shaft 3 are sufficiently separated and installed”
1. If “Fr” is defined as “the lift acting on a point on the circumference where the eccentric distance (radius) from the rotational axis of the airframe constituted by the rotating disk 1 and the airframe body 2 is r”,
A, Fr = (Pb + Pd)-(Pa + Pc).
The following formula is established.
2, “When the rotating disk 1 is not rotating”
B. Since only “atmospheric pressure Pe as static fluid pressure” acts on all point portions of “point 11, point 12, point 13, and point 14”, “Pa = Pb = Pc = Pd = Pe "holds,
B, therefore, “Fr = (Pb + Pd) − (Pa + Pc) = 0”, and “lift” is not generated even in the entire aircraft.
C, this aircraft will not surface.
3. “When the rotating disk 1 is rotating”
B) Since the rotation speed is the same, “atmospheric pressure as kinetic fluid pressure acting on points 11 and 12 which are one point on the upper and lower surfaces of the rotating disk 1”, that is, “Pa · Pb” is the same value. Since both are lower than the “atmospheric pressure Pe around the aircraft” according to Bernoulli's theorem, the equation “Pa = Pb <Pe” holds.
On the other hand, “atmospheric pressure as stationary fluid pressure acting on points 13 and 14 which are one point on the upper and lower surfaces of the airframe body 2 which is stationary with respect to space”, that is, “Pc · Pd” is the same value. Since both are the same pressure as the “atmospheric pressure Pe around the aircraft”, the formula “Pc = Pd = Pe” holds.
C, that is, the equation of “Pa = Pb” <“Pc = Pd = Pe” is established from “the equation of Lee and Lo”.
D. Also, since “Fr = (Pb + Pd) − (Pa + Pc)”, the mathematical expression “Fr = (Pb−Pa) + (Pd−Pc) = 0” is established.
Therefore, “lift” is not generated in the “one point portion on the circumference where the eccentric distance (radius) from the rotation axis of the airframe constituted by the rotating disk 1 and the airframe body 2 is r”. Therefore, “the lift is not generated even in the entire aircraft”
F. No matter how fast the rotating disk 1 is rotated, this aircraft will not rise.

“The upper rotating disk 1 and the lower machine body 2 connected by the rotating shaft 3 are installed sufficiently close to each other, and the lower surface 6 of the rotating disk 1 and the upper surface of the machine body 2 which are installed in parallel to the plane are smoothed. In “FIG. 5” as a “schematic diagram of the case where the distance between both surfaces of the circular surface 7 is“ installed so as to be so narrow that both surfaces do not contact ”,
1. If “Fr” is defined as “the lift acting on a point on the circumference where the eccentric distance (radius) from the rotational axis of the airframe constituted by the rotating disk 1 and the airframe body 2 is r”,
A, Fr = (Pb + Pd)-(Pa + Pc).
The following formula is established.
2, “When the rotating disk 1 is not rotating”
B. Since only “atmospheric pressure Pe as static fluid pressure” acts on all point portions of “point 11, point 12, point 13, and point 14”, “Pa = Pb = Pc = Pd = Pe "holds,
B, therefore, “Fr = (Pb + Pd) − (Pa + Pc) = 0”, and “lift” is not generated even in the entire aircraft.
C, this aircraft will not surface.
3. “When the rotating disk 1 is rotating”
“Both of the lower surface 6 of the rotating disk 1 and the smooth circular surface 7 of the upper surface of the airframe body 2 are installed in parallel to each other and the distance between them is very narrow.” In the “space as the gap between the two surfaces”, “the air pressure acting on both surfaces, that is, Pb / Pc as the air pressure at points 12 and 13” is equal because of the viscous nature of the air. The formula “Pb = Pc” is established.
B) On the other hand, “the point 11 which is a point on the surface 5 of the upper surface 5 of the rotating disk 1” is moving with respect to the atmosphere, so “the value of the pressure Pa acting at this point 11” Naturally, the fluid pressure is smaller than the atmospheric pressure Pe, and therefore, the formula “Pa <Pe” is established.
C. Also, since “the point 14 which is one point on the lower surface 8 of the airframe body 2” is not moving with respect to the atmosphere, “the value of the atmospheric pressure Pd acting at this point 14” is naturally This is equal to “atmospheric pressure Pe as static fluid pressure”, and the formula “Pd = Pe” is established.
D. Here, “Fr = (Pb + Pd) − (Pa + Pc)”, and therefore, from “Pb = Pc”, “Pa <Pe”, and “Pd = Pe” as three types of equations in Lee Lo Ha Fr = (Pd−Pa)> 0 ”is established.
E. Therefore, “lift Fr” is generated at “one point portion on the circumference where the eccentric distance (radius) from the rotation axis of the airframe constituted by the rotating disk 1 and the airframe body 2 is r”. Therefore, lift is also generated in “the entire upper surface 5 of the rotating disk 1 and thus also the entire body”, and if the rotating disk 1 is rotated at a sufficiently high speed, the body can be lifted.
F. “The value of this lift force Fr”, that is, “Let the airframe rise at a point on the circumference where the eccentric distance (radius) from the rotational axis of the airframe constituted by the rotating disk 1 and the airframe body 2 is r. The “upward force value” is “(Pd−Pa) value”, whereas “Pd value” is “atmospheric pressure value Pe constant”, whereas “Pa value” is According to Bernoulli's theorem, the higher the rotational speed of the rotating disk 1 is, the smaller it is. Accordingly, the “value of lift Fr” is increased as the rotating speed of the rotating disk 1 is increased.
From the inferences of G, A to F and the results, if the rotating disk 1 is rotated at a sufficiently high speed “until the sum of the lift forces acting on the entire upper surface 5 of the rotating disk 1 exceeds the total weight of the fuselage”, this “ The “disk lift type flying object” will rise, and the “present invention” will be established.
4. That is, in this “disk lift type flying object”, “rotation speed of the rotating disk 1” is set to “i”, and “total sum of lift acting on the entire upper surface 5 of the rotating disk 1” exceeds the total weight of the aircraft. If you lift it, the aircraft will surface,
B) If the “total lift acting on the entire upper surface 5 of the rotating disk 1” is maintained in a state where it is equal to the total weight of the aircraft, the aircraft will stop in the air (hovering state),
C. If the "total lift acting on the entire upper surface 5 of the rotating disk 1" is lowered to a level that does not exceed the total weight of the aircraft, the aircraft will descend.
5. Based on the above facts, this “disk lift type flying vehicle” can be freely adjusted to “increase, stop and descend in the air” by adjusting the rotation speed of the prime mover 4 and adjusting the “rotation speed of the rotating disk 1”. Therefore, the practicality of the “aircraft capable of vertical takeoff and landing” is established, and the “present invention” is established.

  About the effect of this invention, it is as the following 1-7.

1. The present invention
B. In response to ““ atmospheric pressure as static fluid pressure due to atmospheric pressure ”acting on the lower surface 8 of the airframe body 2”
B) By rotating the rotating disk 1 at the upper part of the airframe body 2 at a high speed, an “motion generated due to a difference in the moving speed from the stationary atmosphere” is generated on the upper surface 5 of the rotating disk 1 which is a contact surface with the atmosphere. `` Atmospheric pressure as fluid pressure ''
C, “the pressure difference as the sum of the relative pressure differences acting on the entire lower surface 8 of the machine body 2 and the upper surface 5 of the rotating disk 1”, or “the former pressure is relatively high and the latter pressure It is a “disk lift type flying vehicle” that uses the “pressure difference generated by the relatively low pressure” as “lift” to lift the entire aircraft.
2. Therefore, with regard to “the levitation principle in this disk lift type aircraft”
B) “To make a strong downdraft using a rotor, jet engine, propeller, and ducted fan, and to use the reaction to lift the aircraft,”
B) During the vertical take-off and landing movement, there is no “wind as a downdraft” around the aircraft, so there is no “wind pressure damage” in which nearby objects are blown away or dust rises.

3. This “disk lift aircraft” is not an “aircraft that uses a rotor, jet engine, propeller, or ducted fan to vertically take off and land”.
Therefore, the “noise” generated in the airframe during vertical takeoff and landing is “atmospheric friction sound generated on the upper surface 5 of the rotating disk 1” and “engine sound of the prime mover 4 that drives the rotating shaft 3 inside the airframe” In addition, the volume of the former is not basically high, and the volume of the latter can be sufficiently reduced by installing a silencer in the aircraft.
B. Therefore, it does not mean that the noise is so terrible like a helicopter not only during takeoff and landing but also when flying low.

4. In this “disk lift type flying object”, the member that lifts the entire weight of the aircraft in the air is “rotating disk 1”, but regarding “the structure of this rotating disk 1”,
B. As clearly shown in FIG. 3, the upper surface 5 has a “conical shape with a raised central portion”, its lower surface 6 has a “planar shape”, and both have a “smooth surface”. Is required, but
B) The “internal structure” is generally “a hollow structure with a thin end of the disk and a thick central part of the disk”, and the hollow structure can be freely combined with girders and beams. Sufficient reinforcement from the inside of the upper and lower surface portions and the entire rotating disk can be achieved while keeping the weight light.
C. Therefore, “the aircraft that has sufficient strength not only for the rotating disk 1 but also for the entire aircraft”, that is, “the elongated helicopter aircraft that must support the weight of the aircraft with a poorly weight-supporting member such as an elongated rotor” A large aircraft with a powerful loading capacity that cannot be compared with.
5. In addition, in this “disk lift type aircraft”
B. Not only when only one rotating disk 1 is mounted, but also "several rotating disks 1 are connected in series in the front / rear direction and left / right direction on the top of the aircraft, corresponding to two, three, and four units respectively.・ It is also possible to increase the lift value of the entire fuselage by installing it appropriately in parallel and in a plane arrangement '', so it is possible to easily enlarge the fuselage,
B) “Large aircraft with a loading capacity of about 100 passengers and cargo of several tens of tons” can be easily obtained.
6. On the contrary, if a light weight and high strength material such as carbon fiber is used to reduce the weight of the entire aircraft, a “small aircraft capable of vertical take-off and landing with only human power as a power source” can be obtained.

7. In this “disk lift aircraft”
The shape of the upper surface 5 of the rotating disk 1 is a gentle conical shape and the lower surface 6 has a planar shape and is in close contact with the smooth circular surface 7 on the upper surface of the fuselage body 2. The “outer shape of the entire aircraft including the rotating disk 1 and the aircraft body 2” is composed entirely of a “curved surface that is smoothly formed so as to be a streamlined shape”, and it is like an existing helicopter rotor. There are no protrusions or deformed parts that cause significant air resistance during forward flight.
Therefore, there is no “aerodynamic factor that causes significant air resistance during forward flight” on the entire outer shape of the aircraft, and it is easy to install a normally used jet engine as a “propulsion engine for the forward direction”. High-speed flight of about 500 km / h or more is possible.

  The “best mode for carrying out the invention” is as follows.

1. The basic outline and structure of the present invention, that is, the “disk lift type flying vehicle”, as shown in FIG. 1 and FIG. 2, are generally as follows.
B. Above the fuselage body 2 is provided a “rotary disk 1 having a conical shape with a raised central part”.
B) “Crew seat in front of aircraft” “Aircraft tail left / right adjustment propeller 10 in aircraft tail” and “Guest room and cargo compartment in the center of aircraft” so that the center of gravity of the aircraft is in the vicinity of the rotation axis of the rotary shaft 3 Perform weight distribution.
C. The outer shape of the entire aircraft shall be “a streamlined shape without protrusions or irregularities that cause air resistance during forward flight”.

2. Regarding “Motor 4” in this “disk lift aircraft”
B) “Rotary force generating mechanism such as turbo-bloom engine, piston engine, electric motor” is connected directly to the rotating shaft 3 or indirectly through a rotation transmitting member, and the rotating shaft 3 is connected by the generated rotating force. A mechanism to rotate.
Or “turbine blades fixed to the rotating shaft 3 or turbine blades fixed to the rotating disk 1” or “turbine that applies rotational force to the rotating shaft 3 via the rotation transmission member connected to the rotating shaft 3”. A mechanism that rotates the rotating shaft 3 and the rotating disk 1 by applying a “high-speed air flow generated by using a jet engine, a turbo flop engine / piston engine, and a propeller / fan associated therewith”.
C, or “a human power mechanism that applies a rotational force to the rotating shaft 3 directly or indirectly through a rotation transmitting member using leg strength, arm force, or the like”.

3. This “disk lift type flying vehicle” cannot take a movement method like “helicopter that moves the aircraft in the tilted direction by tilting the rotor forward, backward, left and right”.
4. Therefore, in particular, in order to fly the aircraft at high speed forward, a “jet engine or turbo flop engine as a propulsion generator is provided at appropriate positions such as the left and right parts, the lower part, the rear part, etc.・ It is necessary to install a piston engine and associated propellers and fans.
5. In addition, in order to move the aircraft freely forward and backward, left and right in the air stop state, or to change the direction of the aircraft freely during the air stop or forward flight,
B. A propeller, fan, or jet engine fumarole that freely changes its direction in the four directions of the aircraft and generates thrust.
B. Propellers, fans, or jet engine vents that are fixedly installed in the four directions of the aircraft and generate thrust.
C. Propeller or fan as “aircraft tail left-right motion adjustment propeller 10” that controls “reverse rotational motion of the aircraft as a reaction reaction of the rotational motion of the rotating disk” in the same way as a conventional helicopter at the aircraft tail Jet engine fumarole.
May be provided.

6. When there is one rotating disk 1, in order to cancel the “gyro effect” acting on the airframe due to the rotation of the rotating disk 1 and to make the flying motion free, A counter rotating disc having the same rotational moment as the rotational moment generated by the rotary disc 1 by rotating in the opposite direction about the same rotational axis 3 may be installed and operated.
7. Regarding “arrangement arrangement of disks when there are a plurality of rotating disks 1”,
In the case of two units, two units are arranged in series in the front-rear direction or the left-right direction on the top surface of the aircraft.
In the case of three units, arrange the three units in series in the front-rear direction or the left-right direction on the upper surface of the fuselage, or arrange them in a triangular shape when viewed from above.
In the case of four units, arrange four units in series in the front-rear direction or the left-right direction on the upper surface of the aircraft, or arrange them in a quadrilateral shape when viewed from above.
In the case of five or more units, the disks are arranged in series in the front-rear direction or the left-right direction on the upper surface of the airframe, or arranged so as to have a radix side shape of the disk when viewed from above.
In addition, in order to cancel the “gyro effect” acting on the aircraft due to the rotation of the rotating disk 1 and to make the flying movement free, the base of the rotating disk 1 is “an even number group consisting of two units”. Both rotating disks have the same shape, structure, and scale in order to have the same rotational moment, and in order to cancel out the gyro effect that both act on the aircraft, It is desirable to have a structure that rotates in the reverse direction at a speed.

8. To maintain lateral stability during forward flight, and to obtain “lift other than lift by rotating disk 1” during forward flight, it is “used in conventional aircraft” on the left and right sides of the body 2. May be provided.
9. To maintain stability during flight and to freely change the direction up, down, left, and right, behind the fuselage main body 2 "the horizontal and vertical tails and those used in conventional aircraft An accompanying elevator or rudder may be provided.

10, “Space as a plane-parallel gap formed by both the lower surface 6 of the rotating disk 1 and the smooth circular surface 7 of the upper surface of the machine body 2 installed so that the distance between them is extremely narrow”. The value of atmospheric pressure as the kinetic fluid pressure that acts equally on both surfaces of the lower surface 6 of the rotating disk 1 as the upper surface of this space and the smooth circular surface 7 of the upper surface of the airframe body 2 as the lower surface. In order to make the value of air resistance acting on the surface as small as possible,
(A) The “space as a plane-parallel gap” may be hermetically sealed and the interior thereof may be “vacuum state or extremely low pressure air state”.
(B) This “space as a plane-parallel gap” may be hermetically sealed and “low specific gravity gas such as hydrogen gas, helium gas, hot air” may be enclosed therein.

11. This “disk lift aircraft”
B. Aircraft that transports passengers and cargo.
B. A small, unmanned model that can be used for radio-controlled flight and autonomous flight.
C. A rotating disk using a light and small engine or electric motor, turning a dedicated handle that rotates the rotating shaft 3, or pulling the strap wound around the rotating shaft 3 by hand “Flying toy with a disk diameter of about 30 cm” that rotates 1 at high speed.
Any of them can be practically used.

In the present invention, that is, the “disk lift type flying object”, the vertical takeoff and landing effect as described above is obtained.
1. Sufficient use and convenience as a “new vertical take-off and landing aircraft replacing the helicopter that occupies the majority of conventional vertical take-off and landing aircraft” will be obtained.
2. Furthermore, it is not only a “small aircraft with several passengers”, but also “a large aircraft with a capacity of about 100 passengers or a weight of about 10 tons or more, and a vertical take-off and landing capable of high-speed flight of about 500 km / h or more. By having a "machine"
B. There is no need for a large airfield and airport in the suburbs, and if there is an appropriate land space, it is possible to take off and landing freely in the center of a big city,
B) Since the aircraft will fly vertically until the aircraft reaches a specified altitude, the noise problem will be solved by limiting the noise range to the vicinity of the landing area,
Therefore, a great deal of convenience can be obtained in terms of time, distance, economics and environment when transporting passengers and cargo.
3. “Practical work such as aerial photography, surveillance flight, spraying of pesticides, transporting small packages” can be performed as “a small, unmanned model that can be used for radio-controlled flight and autonomous flight” You can enjoy competitive flight, aerobatics, etc.
4. As a “flight toy with a disk diameter of about 30 cm”, it can be enjoyed not only in adults but also in children, and in flight and operation not only outdoors but also indoors.
5. For the above reasons, the present invention has great industrial applicability.

Is the side view of the airframe of this disk lift type aircraft. Is a plan view of the airframe of this disk lift type aircraft. Is a sectional view with the rotational axis of each part of the rotating disk 1 of the present disk lift type flying body 1 and the upper surface of the airframe body 2 and the bearing member 9 as the cutting surface, and "the rotating shaft 3 and the prime mover". 4 side view ". Is a “schematic diagram for explaining the state of lift generated in this disk lift type flying vehicle”, “the upper rotating disk 1 connected by the rotating shaft 3 and the lower airframe body 2 are sufficient. Schematic diagram when installed separately. " Is a “schematic diagram for explaining the state of lift generated in this disk lift type flying vehicle”, “the upper rotating disk 1 connected by the rotating shaft 3 and the lower airframe body 2 are sufficient. The distance between both the lower surface 6 of the rotating disk 1 and the smooth circular surface 7 of the upper surface of the machine body 2 which are installed close to each other and parallel to the plane is “so narrow that both surfaces are not in contact with each other. "Schematic diagram of when installed"

1 is a rotating disk. 2 is the body of the aircraft. 3 is a rotating shaft. 4 is the prime mover. 5 is the upper surface of the rotating disk 1. 6 is the lower surface of the rotating disk 1. 7 is a smooth circular surface on the upper surface of the body 2. 8 is a lower surface of the body 2. 9 is a bearing member of the rotating shaft 3. Reference numeral 10 denotes a propeller that adjusts the lateral movement of the aircraft tail.
11 is a point on the “upper surface 5 of the rotating disk 1” that “the eccentric distance from the rotational axis is r”.
12 is one point on the “lower surface 6 of the rotating disk 1” that “the eccentric distance from the rotational axis is r”.
13 is a point that “the eccentric distance from the rotational axis r is” on the “smooth circular surface 7 of the airframe body 2”.
Reference numeral 14 is a point on the “lower surface 8 of the main body 2” that “the eccentric distance from the rotational axis is r”.

The present invention
1. Its main structure is
A rotating disk 1 which is located above the body body 2 and rotates with the “rotary shaft 3 held by the bearing member 9 in the body body 2” as a rotation axis.
B. A rotating shaft 3 having a rotational axis centered on the center of the rotating disk 1 is held by the bearing member 9 and is “this rotating shaft 3 for rotating the rotating disk 1”. A motor 4 that gives a rotational force to the shaft or a turbine mechanism that gives a rotational force to the rotary shaft 3 using a high-speed air flow or a human-powered mechanism that gives a rotational force to the rotary shaft 3 using a leg arm force or the like is installed. Airframe body 2.
Composed of two kinds of members
2. “Smoothly-formed bottom surface 6 of rotating disk 1” and “the bottom surface 6 of this rotating disk 1 have substantially the same diameter, and are installed on the bottom surface 6 of this rotating disk 1 in the nearest opposite plane and Ri I to the smooth formed shape to set very narrow in the upper and lower surfaces of the gap between the "machine smooth circular surface 7 of the upper surface of the main body 2""to the extent that it does not contact" both above and below the plane ",
3. “The upper surface of the space as the gap between the upper and lower surfaces, that is, the lower surface 6 of the rotating disk 1 and the lower surface of the space as the gap between the upper and lower surfaces, that is, the lower surface of the main body 2, which is generated by rotating the rotating disk 1 at high speed. Making each of the atmospheric pressures as kinetic fluid pressures generated and acting on both surfaces of the smooth circular surface 7 of the upper surface equal or sufficiently approximate,
4. Thus, “actually generated on the upper surface 5 of the rotating rotating disk 1 and acting on the lower surface 8 of the airframe body 2 and“ atmospheric pressure as a kinetic fluid pressure generated due to a difference in motion speed from the stationary atmosphere ”. `` Relative pressure difference between both atmospheric pressures of atmospheric pressure as static fluid pressure due to atmospheric pressure '', that is, `` pressure difference generated when the former atmospheric pressure is relatively low and the latter atmospheric pressure is relatively high ”Is used as“ lifting force ”and the“ whole body composed of the rotating disk 1 and the airframe body 2 ”is levitated upward,
5. By adjusting “the magnitude of the rotational speed of the rotating disk 1 generated by the adjustment operation of the rotational speed of the prime mover 4, that is, the strength of the lift acting toward the upper part of the aircraft”, the “rising and descending in the vertical direction and the air It is a “disk lift type air vehicle” characterized in that it can freely perform a stop motion and thus a vertical take-off and landing motion.

Claims (1)

Its main structure is “a rotating disk that rotates at the top of the fuselage main body and rotates about the rotation axis held by the bearing member on the fuselage main body” and “the center of the rotating disk at the bottom of this rotating disk” A rotating shaft with the rotating shaft centered on is held by a bearing member, and a rotational force is applied to the rotating shaft by using a prime mover or a high-speed air flow that applies a rotating force to the rotating shaft to rotate the rotating disk. It is composed of two types of members, “the main body of the machine body that has a human power mechanism that gives a rotational force to this rotating shaft using a turbine mechanism or leg arm strength, etc.”
“The lower surface of a rotating disk that has been formed smoothly” and “The machine body, which has the same diameter as the lower surface of this rotating disk, is placed in parallel on the opposite surface of the rotating disk and is formed in a smooth manner. "Smooth circular surface of the upper surface of the upper surface of the upper and lower surfaces" and the gap between both upper and lower surfaces should be set so narrow that the upper and lower surfaces do not contact each other. By `` vacuum state / extremely low pressure air state '' or by `` sealing the gap between the upper and lower surfaces and enclosing low specific gravity gas such as hydrogen gas, helium gas, hot air etc. in the space as this gap ''
"Surface of both the upper surface of the space as the gap between the upper and lower surfaces, that is, the lower surface of the rotating disk and the lower surface of the space as the gap between the upper and lower surfaces, that is, the smooth circular surface of the upper surface of the machine body, which are generated by rotating the rotating disk at high speed. `` Each atmospheric pressure as kinetic fluid pressure generated and acting on each ''
Therefore, “the atmospheric pressure as the kinetic fluid pressure generated due to the difference in motion speed from the stationary atmosphere” acting on the upper surface of the rotating rotating disk and the “static fluid pressure due to atmospheric pressure acting on the lower surface of the aircraft body” The relative pressure difference between both atmospheric pressures ”, that is, the“ pressure difference generated when the former atmospheric pressure is relatively low and the latter atmospheric pressure is relatively high ”is used as“ lift ”. The `` whole body composed of a rotating disk and the fuselage body '' is levitated upward,
By adjusting the magnitude of the rotational speed of the rotating disk caused by the operation of adjusting the rotational speed of the prime mover, that is, the strength of the lift acting toward the upper part of the aircraft, the movement of vertical ascent and descent and air suspension A disk lift-type flying object characterized by enabling "vertical take-off and landing movement" freely.

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