JPH04215596A - Helicopter - Google Patents

Abstract

PURPOSE:To provide a helicopter with improved performance by forming its main rotor blade from a movable part and a base, and equipping variability for the dia. of main rotor under flight. CONSTITUTION:A helicopter according to the present invention is composed of a main rotor blade consisting of a movable part 15 and base 14, an actuator 17 to move the movable part 15 relative to the base 14, an oil-hydraulic device 18, and switch to control the motion. According to the above constitution, the dia. of the main rotor can be changed under the flight.

Description

[Detailed description of the invention]

0001

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a helicopter whose main rotor has a variable diameter.

0002

BACKGROUND OF THE INVENTION Conventional helicopter main rotors have a constant blade length. Therefore, the diameter of the main rotor is also
~As shown in FIG. 25, the flapping angle remained constant unless changed, rotated around the rotation axis 3, and did not change.

0003

BACKGROUND OF THE INVENTION Helicopters have a wide range of flight ranges, from hovering flight to forward flight. During hovering flight, as shown in FIG. 22, it is necessary to support the weight W of the aircraft with the lift force T of the main rotor. The lift force T of the main rotor during hovering is T=(ρπR2 V)・2V=W
It is expressed as (1). However, ρ = air density R = radius of main rotor (proportional to main rotor blade length)
V = Induced speed at main rotor surface (downflow) From formula (1), V2 = T/2ρπR2 = W/2ρπR2
(2)

[0004] Increasing the induced velocity V imparts large kinetic energy to the air flowing out of the main rotor, increasing vortex losses and reducing the efficiency of the main rotor. Therefore, in order to improve the hovering performance, it is necessary to increase the rotor radius R and decrease the induced speed V, as seen from equation (2).

On the other hand, the air speed with respect to the main rotor blades during forward flight is a combination of the speed due to rotation and the speed due to forward movement, so the blades on the forward side have a large relative speed to the air as shown in FIG. , a shock wave is generated on the upper surface of the blade tip, resulting in a reduction in lift and an increase in drag, which deteriorates the aerodynamic characteristics of the rotor. Therefore, a long blade length of the main rotor is good for hovering flight performance, but is disadvantageous for high-speed forward flight performance. An object of the present invention is to provide a helicopter that solves these problems.

[0006]

[Means to solve the problem] (First means)

[0007] The helicopter according to the present invention includes a main rotor blade consisting of a movable part and a base part, means for moving the movable part with respect to the base part, and a switch for operating the movement. It is characterized by being able to change the diameter of the main rotor. (Second means)

[0008] In the first means, the helicopter according to the present invention includes a sensor for detecting flight conditions and operating conditions of the helicopter, and a signal from the sensor is inputted to input a control signal for a movable part of a main rotor blade to the main rotor. It is characterized by being equipped with a computer that outputs output to the means for moving the movable part of the blades, and being able to automatically change the diameter of the main rotor during flight.

[0009]

[Operation] The main rotor blade of the helicopter consists of a movable part and a base part, and the main rotor By changing the diameter of the plane, it is possible to fly under the optimum conditions for each flight condition.

[0010] The moving means can be controlled by a pilot's switch operation. Furthermore, by providing sensors and computers that detect flight conditions, etc., movement of the movable parts can be automatically controlled. Therefore, the diameter of the main rotor can be changed during flight to fly under the optimal conditions for each flight condition.

[0011]

Embodiment A first embodiment of the present invention is shown in FIGS. 1 to 7.

FIG. 1 is a view of the first embodiment of the present invention seen from above, FIG. 2 is a view of the main rotor (large diameter) according to the first embodiment, seen from the rear, and FIG. 3 is a view of the first embodiment of the invention. FIG. 4 is an operation block diagram of the first embodiment, FIG. 5 is a view of the main rotor diameter (large, small) as seen from above, and FIG. 6 is a view of the main rotor (small diameter) as seen from the rear. FIG. 7 is a cross-sectional view of the helicopter according to the embodiment as seen from the side, and FIG. 7 is a cross-sectional view of the helicopter of the first embodiment as seen from the front.

The movable part 15 provided outside the base part 14 of the main rotor blade is moved via a rod 16 by the power of an actuator 17 and a hydraulic system or an electric motor 18, as shown in FIG.
and is driven as shown in FIG. 3, changing the main rotor within the range from a large diameter (FIG. 2) to a small diameter (FIG. 3).

The movable portion 15 is driven as follows. When the pilot operates a switch, an electric signal is transmitted to the hydraulic device or electric motor 18 through the wiring 19, actuating the hydraulic device or electric motor 18 and the actuator 17, and driving the movable part 15 via the rod 16. The pilot operates the switch 23 at his discretion while monitoring the flight status of the helicopter. These operating processes are shown in the operating block diagram of FIG.

FIG. 5 shows the state in which the main rotor has a large diameter and the state in which it has a small diameter when viewed from above. The arrangement of the components of the first embodiment and the connections between these components are shown in FIGS. 6 and 7. Note that the gap between the fixed part and the movable part is sealed with elastic rubber, synthetic fiber material, etc. (Sealing is performed in the same manner in the following embodiments.) A second embodiment of the present invention is shown in FIGS. 8 to 10.

FIG. 10 is an operational block diagram of a second embodiment of the present invention, FIG. 8 is a sectional view of the helicopter of the second embodiment seen from the side, and FIG. 9 is a sectional view of the helicopter of the second embodiment seen from the front. Show the diagram.

In the first embodiment, since the pilot operates the switch, the workload of the pilot 22 is heavy. The second embodiment reduces the pilot's workload.

A sensor 24 mounted on the helicopter detects the flight status and operating status of the helicopter necessary for controlling the movable part of the main rotor 2, such as the flight speed of the helicopter and the number of revolutions of the main rotor. 26. The computer 26 controls the movable part 15 of the main rotor blade based on the data signal from the sensor 24, that is, calculates the optimum value of the movement 21 of the movable part 15, and sends the control signal for the movable part to the hydraulic system or the electric motor 18 through the wiring 27.
and the actuator 17, and with these powers,
The movable part 15 is driven via the rod 16 to change the diameter of the main rotor. The arrangement of the constituent elements of the second embodiment, the connection of those constituent elements, etc. are shown in FIGS. 8 and 9. The control method shown in this second embodiment is applicable to all of the first, third, fourth, and fifth embodiments. This control method greatly reduces the workload of the pilot 22. A third embodiment of the present invention is shown in FIGS. 11-14.

FIG. 11 is a top view of a third embodiment of the present invention, FIG. 12 is a sectional view of a main rotor according to the third embodiment, and FIG. 13 is a main rotor (large diameter) according to the third embodiment. Figure 14 shows the main rotor (small diameter) according to the third embodiment.
Shows a view from the rear.

A hydraulic device or an electric motor 18, an actuator 17, a rod 16, etc. are provided inside the main rotor 2 to drive the movable part 29, which is a relatively large part.

The movable part 29 is driven by the power of an actuator 17 and a hydraulic device or an electric motor 18 via a rod 16, and as shown in FIGS. 14). The cross section of the inner side of the main rotor blade is double as shown in FIG. 12, and the movable part 29 moves 21 along the base part 28 existing inside.

The third embodiment uses the method of the first embodiment (operation block diagram in FIG. 4) using the pilot's switch operation, and
It can be driven by any of the automatic methods according to the second embodiment (operation block diagram in FIG. 10). A fourth embodiment of the present invention is shown in FIGS. 15-19.

FIG. 15 is a view of the fourth embodiment of the present invention seen from above, FIG. 16 is a view of the main rotor (large diameter) according to the fourth embodiment, seen from the rear, and FIG. 17 is a view of the fourth embodiment of the present invention. The main rotor (
FIG. 18 is a view of the fourth embodiment seen from above (forward arrangement), and FIG. 19 is a view of the fourth embodiment seen from above (extreme arrangement). A movable part 30 provided on the outside of the base part 28 of the main rotor blade can rotate and move 32 about a hinge 31.

The movable part 30 is driven by the power of an actuator 17 and a hydraulic device or an electric motor 18 via a rod 16, and as shown in FIGS. 17).

Although FIG. 15 shows the case where the movable part 30 moves backward, as shown in FIG.
It is also possible to move forward by rotating and moving 32 around 4, or it is also possible to move the movable part 30 largely and retreat (or move forward) to an extreme position as shown in FIG. If you can move to an extreme position like this,
With more degrees of freedom, the helicopter can perform better.

The fourth embodiment also uses the method of the first embodiment using the pilot's switch operation (operation block diagram in FIG. 4), and the automatic method according to the second embodiment (operation block diagram in FIG. 10).
It can be driven by any of the following. A fifth embodiment of the present invention is shown in FIGS. 20 and 21. FIG. 20 shows a rear view of the fifth embodiment of the present invention, and FIG. 21 shows a top view of the fifth embodiment.

A rotor diameter changing fitting 35 is provided between the rotating shaft 3 and the main rotor 2. This rotor diameter changing fitting 35 has a structure that allows the position of the main rotor 2 to be changed with respect to the rotating shaft 3, and changes the main rotor from a large diameter (indicated by a solid line in FIG. 20) to a small diameter (indicated by a broken line in FIG. 20). ) Move within the range of 36
can.

The rotor diameter changing fitting 35 changes the main rotor blade from the solid line in FIG. 20 (large rotor diameter) to the broken line in FIG. can move within a range. In the fifth embodiment, the movable part of the main rotor blade is composed of a rotor diameter changing metal fitting 35 and a blade part 37. In this case, the base portion becomes the hinge 38 that attaches the rotor diameter changing fitting 35 to the rotating shaft 3.

The fourth embodiment also uses the method of the first embodiment (operation block diagram in FIG. 4) by the pilot's switch operation, and the second
It can be driven by any of the automatic methods (operation block diagram in FIG. 10) according to the embodiments.

[0030]

[Effects of the Invention] Since the present invention is constructed as described above, it produces the following effects.

(1) By changing the diameter of the main rotor, the helicopter can fly in an optimal state for each flight condition. This results in a helicopter that has good performance over the entire flight range and is highly economical.

(2) The movable part that changes the diameter of the main rotor is driven by a sensor, a computer, a hydraulic device, an electric motor, an actuator, etc., and the main rotor diameter can be set to the optimum diameter for each flight condition, reducing pilot work. The burden can be reduced, and a helicopter that has good performance over the entire flight range and is highly economical can be obtained.

[Brief explanation of the drawing]

FIG. 1 is a top view of a first embodiment of the present invention.

[Fig. 2] Main rotor (large diameter) according to the first embodiment of the present invention
View from the rear.

[Fig. 3] Main rotor (small diameter) according to the first embodiment of the present invention
View from the rear.

FIG. 4 is an operational block diagram of the first embodiment of the present invention.

FIG. 5 is a view from above of the main rotor (large and small diameter) of the first embodiment of the present invention.

FIG. 6 is a cross-sectional view of the helicopter according to the first embodiment of the present invention, viewed from the side.

FIG. 7 is a sectional view of the helicopter according to the first embodiment of the present invention, viewed from the front.

FIG. 8 is a cross-sectional view of a helicopter according to a second embodiment of the present invention, viewed from the side.

FIG. 9 is a sectional view of a helicopter according to a second embodiment of the present invention, viewed from the front.

FIG. 10 is an operational block diagram of a second embodiment of the present invention.

FIG. 11 is a top view of the third embodiment of the present invention.

FIG. 12 is a sectional view of a main rotor according to a third embodiment of the present invention.

FIG. 13 is a rear view of a main rotor (large diameter) according to a third embodiment of the present invention.

FIG. 14 is a rear view of a main rotor (small diameter) according to a third embodiment of the present invention.

FIG. 15 is a top view of the fourth embodiment of the present invention.

FIG. 16 is a rear view of a main rotor (large diameter) according to a fourth embodiment of the present invention.

FIG. 17 is a rear view of a main rotor (small diameter) according to a fourth embodiment of the present invention.

FIG. 18 is a view from above of the fourth embodiment of the present invention (forward arrangement).

FIG. 19 is a top view of the fourth embodiment of the present invention (extreme arrangement).

FIG. 20 is a rear view of the fifth embodiment of the present invention.

FIG. 21 is a top view of the fifth embodiment of the present invention.

FIG. 22 is a diagram showing the relationship between the weight of the helicopter and the lift force of the main rotor.

FIG. 23 is a diagram showing the relationship between the relative speeds of the main rotor and airflow.

FIG. 24 is a sectional view of a conventional helicopter seen from the side.

FIG. 25 is a top view of a conventional helicopter.

[Explanation of symbols]

1... Helicopter, 2... Main rotor, 3... Rotating shaft, 4... Fuselage, 5... Horizontal stabilizer, 6... Vertical stabilizer, 7... Tail rotor, 8
...Engine, 11...Airflow, 13...Main rotor blade, 1
4... Foundation part, 15... Movable part, 16... Rod, 17... Actuator, 18... Hydraulic device or electric motor, 19... Wiring,
20...Seal, 21...Movement, 22...Pilot, 23...
Switch, 24...Sensor, 25...Wiring, 26...Computer, 27...Wiring, 28...Foundation part, 29...Movable part, 30
...Movable part, 31...Hinge, 32...Movement, 34...Hinge,
35...Rotor diameter changing fitting, 36...Movement, 37...Blade part, 38...Hinge.

Claims (2)

[Claims] 1. A helicopter, comprising: a main rotor blade consisting of a movable part and a base part; means for moving the movable part with respect to the base part; and a switch for operating the movement; A helicopter characterized by being able to change the diameter of its rotor. 2. A sensor for detecting the flight status and operating status of the helicopter; and a computer for inputting signals from the sensor and outputting control signals for the movable part of the main rotor blade to means for moving the movable part of the rotor blade. Helicopter according to claim 1, characterized in that the helicopter is equipped with a main rotor and is capable of automatically changing the diameter of the main rotor during flight.