JP7002793B2 - Manned aircraft - Google Patents

Description

The present invention relates to a manned aircraft.

Patent Document 1 proposes a technique relating to a motorcycle.

Japanese Unexamined Patent Publication No. 2016-210328 JP-A-2015-047965 U.S. Patent Application Publication No. 2016/01/76256

The techniques described in Patent Document 1 and Patent Document 2 move the vehicle body forward by applying the rotational force of the tire to the road or the like, but there is a large amount of energy loss such as frictional force. On the other hand, as in Patent Document 3, a technique has been proposed in which the entire vehicle is flown to reduce such energy loss and to eliminate restrictions on movement.

One object of the present invention is to provide an air vehicle as a new means of transportation.

According to the present invention
With the engine and motor
The first rotor that generates lift by the engine,
A second rotor that generates at least propulsive force in the front-rear direction by the motor, and
A control unit for controlling the engine and the motor.
Hybrid manned aircraft. Is obtained.

According to the present invention, an air vehicle as a new means of transportation can be obtained.

It is a schematic diagram of the flying object according to the embodiment of this invention. It is a functional block diagram of the flying object of FIG. It is another functional block diagram of the flying object of FIG. It is a block diagram by the modification of the flying object by this invention. It is a conceptual block diagram by another modification of the flying object by this invention. It is a conceptual block diagram by another modification of the flying object by this invention. It is a conceptual block diagram by another modification of the flying object by this invention. It is a conceptual block diagram by the power generation mode of the flying object by this invention. It is a conceptual block diagram by the power generation mode of the flying object by this invention. It is a conceptual block diagram by the power generation mode of the flying object by this invention. It is a conceptual block diagram by the power generation mode of the flying object by this invention.

The contents of the embodiments of the present invention will be described in a list. The flying object according to the embodiment of the present invention has the following configurations.
[Item 1]
With the engine and motor
The first rotor that generates lift by the engine,
A second rotor that generates at least propulsive force in the front-rear direction by the motor, and
A control unit for controlling the engine and the motor.
Hybrid manned aircraft.
[Item 2]
The hybrid manned aircraft according to claim 1.
With the generator connected to the engine
Further equipped with a battery for storing the electric power generated by the generator.
Hybrid manned aircraft.
[Item 3]
The hybrid manned aircraft according to claim 2.
Further equipped with a power supply terminal for supplying the stored electric power to the outside,
Hybrid manned aircraft.
[Item 4]
The hybrid manned aircraft according to claim 3.
The control unit stops the rotation of the first rotary wing unit while supplying the electric power to the outside.
Hybrid manned aircraft.
[Item 5]
The hybrid manned aircraft according to any one of claims 2 to 4.
The motor receives power from the battery.
Hybrid manned aircraft.
[Item 6]
The hybrid manned aircraft according to claim 2 to 5.
The battery is charged by utilizing at least the regenerative power generated by the second rotary wing portion during deceleration of the hybrid manned vehicle.
Hybrid manned aircraft.
[Item 7]
The hybrid manned aircraft according to any one of claims 1 to 6.
The control unit uses the second rotary wing unit to control the attitude at least in the horizontal direction.
Hybrid manned aircraft.
[Item 8]
The hybrid manned aircraft according to any one of claims 1 to 7.
Each of the first rotary wing portions includes a front side first rotary wing portion and a rear side first rotary wing portion that generate propulsive force at least in the vertical direction.
The second rotary wing portion is a front side second rotary wing portion provided on each of the front left and right sides, and a rear side second rotation provided on each of the rear left and right sides, each of which generates a propulsive force at least in the horizontal direction. Equipped with wings,
Hybrid manned aircraft.
[Item 9]
The hybrid manned aircraft according to any one of claims 1 to 8.
The first rotor is a counter-rotating propeller.
Hybrid manned aircraft.
[Item 10]
The hybrid manned aircraft according to any one of claims 1 to 9.
It is equipped with wheels provided at the bottom of the hybrid manned aircraft.
It is possible to run using the wheels under predetermined conditions.
Hybrid manned aircraft.

<Details of the embodiment>
Hereinafter, the flying object according to the embodiment of the present invention will be described with reference to the drawings.

<Overview>
The flying object 1 according to the embodiment of the present invention is a flying object on which a person can ride, and may be called a so-called hoverbike, exercise bike, or the like. Aircraft 1 is 5 on the ground with a person on it.
It is possible to levitate and move at a height of about 0 cm to 100 cm.

<Flight mode>
As shown in FIG. 1, the flying object 1 according to the present embodiment includes a main body portion 2 that is long in the front-rear direction. The main body 2 includes two propellers 4 and four propellers 5. The propeller 5 according to the present embodiment is used to levitate the flying object 1 in the vertical direction.
The propeller 4 is mainly used for moving forward, backward, turning, and the like of the flying object 1.

One propeller 5 is provided in the front and rear. The propeller 5 rotates under the power of an engine (not shown). As the propeller 5 rotates, the flying object 1 takes off from the ground. The propeller 5 can rotate to the right, stop, and rotate to the left. The propeller 5 according to the present embodiment has a diameter of 1.5 m.

Propellers 4 are provided at two locations on the left and right sides on the front side and two locations on the left and right sides on the rear side, for a total of four locations. The propeller 4 rotates under the power of the motor 6. Propeller 4
Generates thrust in the front-back direction. As a result, the flying object 1 can move forward and backward. Further, when the flying object 1 is surfaced by the propeller 5 described above, the propeller 4 is changed to the flying object 1.
It has a function to control the attitude of (details will be described later).

The propeller 5 according to the present embodiment is a so-called counter-rotating propeller that rotates two sets of upper and lower propellers in opposite directions. Further, the number of arbitrary blades (rotors) having an elongated shape in both the propeller 4 and the propeller 5 (for example, 1, 2, 3, 4, or more blades) may be used.
Further, the shape of the blade can be any shape such as a flat shape, a curved shape, a twisted shape, a tapered shape, or a combination thereof.

The shape of the blade can be changed (for example, expansion / contraction, folding, bending, etc.). The blades may be symmetrical (having the same upper and lower surfaces) or asymmetric (having differently shaped upper and lower surfaces). The blades can be formed into an air wheel, wing, or geometry suitable for generating dynamic aerodynamic forces (eg, lift, thrust) as the blades move through the air. The geometry of the blades can be appropriately selected to optimize the dynamic air characteristics of the blades, such as increasing lift and thrust and reducing drag. Further, in the present embodiment, both fixed pitch and variable pitch can be adopted.

The blades can all rotate in the same direction or can rotate independently. The other blades rotate in the other direction. The blades can all rotate at the same rotation speed,
It is also possible to rotate at different rotation speeds. The rotation speed can be automatically or manually determined based on the dimensions (for example, size, weight) and control state (speed, moving direction, etc.) of the moving body.

As shown in FIG. 2, the engine P according to the present embodiment is driven by gasoline. The vehicle 1 includes a propeller R (propeller 5) and an engine P, a gasoline tank for supplying gasoline (mixed fuel) to the engine P, a generator that generates electricity by using the power of the engine, and electric power supplied. It is equipped with a power control unit that adjusts.

Further, the flying object 1 includes an inertia sensor (acceleration sensor, gyro sensor), a GPS sensor, a proximity sensor (for example, a rider), or a vision / image sensor (for example, a camera), and the data acquired by the sensor is It is output to the control unit. The control unit calculates the output of the engine and the like using the acquired data.

As shown, the power of the engine P is also supplied to the battery B as electric power through a generator (not shown). The electric power of the battery B is supplied to the motor M, and the propellers Rs (propeller 4) rotate. The battery controller manages the power supply of the battery. Motor M
An ESC (Electronic Speed Controller) is connected to the ESC, and the rotation of the motor is controlled based on the control from the flight controller.

The flight controller is a so-called processing unit. The processing unit can have one or more processors such as a programmable processor (eg, a central processing unit (CPU)). Further, the flying object 1 includes an inertial sensor (accelerometer, gyro sensor), G.
It includes a PS sensor, a proximity sensor (eg, a rider), or a vision / image sensor (eg, a camera), and the data acquired by the sensor is output to the flight controller.

Returning to FIG. 1, when riding and driving on the flying object 1, the user sits on the seat 8 and drives while taking a forward leaning posture.

As shown in FIG. 3, in the present embodiment, the power of the engine P is transmitted to two propellers R (front propeller 5 and rear propeller 5 in FIG. 1), and the propeller R is rotated to rotate the vehicle body 1. Ascend. At the same time, the engine P also supplies power to the two batteries B via a generator (not shown). The battery B supplies electric power to the two motors M, respectively, and rotates a total of four propellers Rs. The number of batteries and the connection relationship are examples, and other configurations may be used.

The rotation speed of the levitation propeller R and the rotation speed of the propeller Rs for attitude control are controlled by the control unit (see FIG. 2). In FIG. 2, the flight controller that controls the motor M is separate from the control unit, but may be integrated.

(Example)
Hereinafter, the specifications of the engine particularly used for the embodiment of the present invention will be described. For the output of the engine, the following formulas 1 and 2 were used as basic formulas.

However, each variable is as follows.

In order for the flying object to surface, the following mathematical formula 3 must hold, and if the mathematical formula 3 is arranged with respect to P, the mathematical formula 4 can be obtained.

In the present embodiment, a propeller having a diameter of 1.5 m and a propeller having a diameter of 2 are used based on the above-mentioned mathematical formula.
.. A 0m propeller was used. The specifications and engine characteristics of each propeller are shown in Tables 1 and 2 below, respectively.

The flying object according to the present invention may be, for example, the processing system shown in FIG. According to the block diagram shown in FIG. 4, the output of the engine P supplies power to the four batteries B via a generator (not shown). The battery B is 2 by supplying electric power to the motor M, respectively.
Rotate one propeller R and four propeller Rs.

Further, with reference to FIGS. 5 to 7, a modification of the power-related block diagram according to the present embodiment will be further described. In the figure, for the sake of simplicity, only one component (motor M, battery B, propeller R / Rs, etc.) is shown, but the required number may actually exist. , The parts may be integrated / separated (integrated / separated) as needed.

The system shown in FIG. 5 is a so-called series system (series system) power engine, as in FIG. 4. In the series method (series method), the engine P is used only for power generation, the power generated by the engine P is supplied to the motor M, and the propeller R / Rs are used only for driving and regeneration. R
/ Rs can charge the storage battery with regenerative energy using the rotational resistance of the propeller (particularly the propeller Rs) when the flying object is decelerating / stopping. It is also possible to store the electric power generated by the surplus electric power generated by the engine P in the battery B.

According to this method, the engine P will be used in areas other than the region where the best fuel consumption rate is obtained (fuel efficiency will deteriorate), but since it is not connected to the propeller R / Rs by a transmission, it will be used.
The most efficient area can be used for the required output.

The system shown in FIG. 6 is a so-called parallel system (parallel system) power engine. The parallel method (parallel method) is a method in which a plurality of mounted power sources are used to drive the wheels. Since the relationship is engine output = torque x number of revolutions, not only is it not possible to obtain sufficient power at low engine revolutions, but efficiency is poor, including idling, and the ability to purify exhaust gas is also reduced. On the other hand, since many motors generate maximum torque at startup, the motor is responsible for a range of harmful emissions due to poor thermal efficiency, which the engine is not good at, such as when starting or suddenly accelerating.
This is a method that takes advantage of both.

In the method shown in FIG. 6, the propellers R / Rs are supplied with power from the engine P or the motor M. In the present embodiment, the transmission has a transmission, through which the propellers R / Rs are driven, and at the same time, power generation (charging) using the motor M is also performed. The motor M, which is also used as a generator for the regenerative brake, is in charge of the range from the start to the medium speed range, and can be adopted even if it is small and has a small output compared to the gross vehicle weight. Therefore, there is an advantage that the capacity of the battery can be reduced. When the remaining battery power is low, it is possible to run with only the engine P over the entire speed range as in a normal internal combustion vehicle. As described above, it is also called a motor assist system because it is mainly composed of a conventional internal combustion vehicle.

It should be noted that this method is generally superior to the series method in terms of installation weight and volume, which can be realized by one motor, and efficiency, such as being able to be directly driven by an engine. However, the structure and control for utilizing the advantages of both power sources are complicated, and there is a drawback that power generation and driving cannot be performed at the same time because of one motor (the charging time becomes shorter as the frequency of use of the motor increases). In addition, the hybrid system itself does not have a function to control the speed, and it requires the same transmission as a normal automobile, which is a drawback that other methods do not have.

The method shown in FIG. 7 is a so-called split method (power split method) in which the propellers R / Rs are used.
Has two methods, one is when the power is directly supplied from the engine P and the other is when the power is supplied from the motor M driven by the battery B to which the power is supplied from the engine P via the generator. ing.

In the split method (power split method), the power from the engine P is split by a power split mechanism using a planetary gear or the like and distributed to the generator and the drive of the wheel, or the drive from the engine P and the motor M. It is a method that can freely synthesize power. When starting or running at low speed, EV running is performed with the electricity stored in the battery B, and during normal running, the engine P is used in the rotation range where the fuel consumption rate is low near the maximum torque, and the battery B is simultaneously generated by the generator via the planetary gear. The speed is controlled while charging the battery. Another feature of this method is that changes in engine output, which cause deterioration in fuel efficiency, are suppressed as much as possible.

The split type uses a power split mechanism (planetary gear) to control the rotation of the generator and motor to give it the role of a transmission, so a conventional transmission is not particularly necessary (it is not impossible to install it). ).

<Power generation mode>
As shown in FIG. 8, the flying object 1 functions as a power generation mode, for example, in the event of a disaster. In this case, for example, the flying object 1 is installed on the ground and supplies various power supplies.

The air vehicle 1 may supply electric power to the outside from the battery B described above (FIG. 3).
Or see FIG. 7). In this case, a terminal for supplying power to the outside may be attached to the battery. Control of power supplied from battery (voltage, current, phase, etc.)
If necessary, a converter may be separately used, and various existing technologies can be applied.

Details will be described with reference to FIGS. 8 to 11. As shown in FIG. 8, the power supplied from the engine P is supplied to a dedicated (separate) battery Bt via a generator (not shown). The battery Bt is provided with a terminal T for external output, and power is supplied to the external device by connecting the external device to the terminal T.

As described above, the engine P is supposed to supply power to the propeller R, but the power supply to the propeller R may be stopped during the power supply. This makes it possible to increase the power supply efficiency.

As shown in FIG. 9, even in a so-called series system (series system) power engine, the electric power generated by the engine P may be supplied to the battery B, and the external terminal T may be attached to the battery B.

As shown in FIG. 10, even in a so-called parallel system (parallel system) power engine, the electric power generated by the engine P may be supplied to the battery B, and the external terminal T may be attached to the battery B.

As shown in FIG. 11, in the so-called split type (power split type) power engine, the external terminal T may be provided in the battery B to which power is supplied from the engine P via the generator.

The embodiments described above are merely examples for facilitating the understanding of the present invention, and are not intended to limit the interpretation of the present invention. It goes without saying that the present invention can be modified and improved without departing from the spirit thereof, and the present invention includes its equivalents.

1 Aircraft 2 Main body 3 Legs 4, 5 Propellers 6 Motors 7 Handles 8 Seats

Claims (2)

The main body, which is formed by extending in the front-back direction,
The first rotary wing portion provided on the main body portion to generate lift, and
Equipped with a second rotary wing that generates propulsive force,
The first rotary wing portion has one front side first rotary wing portion and one rear side first rotary wing portion that generate propulsive force at least in the vertical direction at the front end and the rear end of the main body portion, respectively. I have
The second rotary wing portion is a pair of front side second rotary wing portions provided on the left and right sides of the front side first rotary wing portion, and a pair of rear portions provided on the left and right sides of the rear side first rotary wing portion. The second rotary wing on the side and
A seat for driving across the main body is provided .
The front side first rotary wing portion so that the front side portion of the main body portion straddles the upper part of the front side first rotary wing portion and the rear side portion of the main body portion straddles the upper side of the rear side first rotary wing portion. And the rear first rotary wing portion is provided.
A manned vehicle in which the seat is located above the front first rotor and the posterior first rotor . The manned aircraft according to claim 1,
An engine that supplies power to the first rotor and
A motor that supplies power to the second rotor and
A manned vehicle comprising the engine and a control unit for controlling the motor.

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