JP2735935B2 - Helicopter - Google Patents

Description

The present invention relates to a helicopter, and more particularly to a rotor blade used therein.

[Conventional technology]

10 to 13 show plan views of various rotor blades of a conventional helicopter.

Figure 10 is an old, orthodox shape, which has been applied to low speed helicopters (approximately 100kt maximum speed). It is easy to manufacture and the manufacturing cost is low.

However, there is a demand for a higher speed helicopter, and in a helicopter with a maximum speed of about 200 kt, the forward speed of the helicopter itself and the speed due to the rotation of the rotor are added, and the Mach number approaches 1 on the forward rotor (the rotor speed). The speed is the radius multiplied by the rotation speed, so the speed is highest at the end of the rotor blade.) Shock waves are generated on the upper surface of the rotor at the end of the rotor blade, causing a reduction in lift and an increase in resistance, resulting in aerodynamic characteristics. Worsen.

To improve the aerodynamic characteristics, the helicopter speeds up by making the end of the rotor blade swept back as shown in Fig. 11 to 13 or increasing the swept back like a swept wing of an airplane. Is being implemented.

Although it is difficult to manufacture a rotor blade with a sweepback angle, the manufacturing cost is high, but the helicopter speed is increased (maximum speed 200k
t) is indispensable.

[Problems to be solved by the invention]

The conventional helicopter rotor blade has the following problems to be solved.

That is, the shapes of the conventional rotor blades shown in FIGS. 10 to 13 are all fixed, and the performance of the rotor blades is good under certain flight conditions (speed, rotation speed of the rotor blades, etc.). There was a problem that the flight conditions were not good.

Thus, there has been a demand for a helicopter that has good rotor blade performance under all flight conditions of the helicopter, and therefore has good helicopter performance over the entire flight range, and is highly efficient and economical.

The present invention solves the above-mentioned problems of a conventional helicopter, and has a helicopter that has good helicopter performance over the entire flight range of the helicopter, and is equipped with a rotor blade capable of operating efficiently and economically. The purpose is to provide.

[Means for solving the problem]

The present invention provides, as a means for solving the above problems, a rotor blade having a movable portion provided at an end so that the planar shape of the end can be changed with respect to the fixed portion, a driving unit for driving the movable portion of the rotor blade, It is an object of the present invention to provide a helicopter comprising: a computer for instructing the drive means to drive the movable unit; and a sensor for detecting and inputting flight conditions as arithmetic data to the computer. .

[Action]

The present invention has the following effects because it is configured as described above.

That is, the shape of the end of the rotor blade of the helicopter can be changed during the flight by driving the movable portion by a control command signal of a computer according to the flight conditions such as the flight speed and the rotor rotation speed. For example, when the rotation angle is low, the sweepback angle of the end of the rotor blade is small, and when the rotation speed of the rotor is high, the sweepback angle of the end of the rotor blade is increased, so that the respective performances are exerted. And can be maintained well.

〔Example〕

First to third embodiments of the present invention will be described with reference to FIGS. 3, 8 and 9 are views common to the first to third embodiments, FIG. 3 is an operation block diagram, FIG. 8 is a side view, and FIG.
The figure is a cross-sectional view of FIG. 8 as viewed in the flight direction. To avoid redundancy, the same components as those in the previous embodiment are denoted by the same reference numerals, and description thereof will be omitted.

First, a first embodiment of the present invention will be described with reference to FIGS. FIG. 1 is a view of the rotor blade 16 according to the first embodiment as viewed from above, FIG. 2 is a view of the rotor blade 16 of FIG. FIG. 3 shows an operation block diagram of the first embodiment. In FIGS. 1 and 2, the end of the rotor blade 16 has a double structure, and a movable portion forming the end is provided.
17 and fixed part 18, movable part 17 is center of rotation (pin)
Actuator 20, hydraulic device or electric motor 21 around 19
Rotation and movement 23 by the power of the rotor blade 16
It is configured to be able to change the receding angle 24 of the end of the end.

FIG. 8 is a side view of the helicopter 1 of the first embodiment provided with the rotor blades 16 (25 and 33 to be described later), and FIG. 9 is a cross-sectional view of the helicopter as viewed in the flight direction. Is provided with a switch 10 for controlling the retreat angle 24 of the rotor blade 16 and, more specifically, the movable portion 17 thereof, and is operated by the pilot 9 as described later. Reference numeral 11 denotes a sensor, such as a flight speed of the helicopter 1, a rotation speed of the rotor blade 16, and the like.
The flight conditions necessary for controlling the end of the rotor blade 16 are detected and input to the computer 14 described later. Reference numeral 14 denotes a computer which controls the rotor blade 16 based on a data signal from the sensor 11 by operating the switch 10, that is, calculates an optimum value of the retreat angle 24 of the movable part 17. In addition, auxiliary members such as wiring will be described together with the description of the operation.

In addition, 3 is a rotating shaft, 4 is an engine, 5 is a fuselage, 6 is a tail rotor, 7 is a vertical tail, and 8 is a horizontal tail.

 Next, the operation of the above configuration will be described.

Helicopter 1 of the first embodiment provided with rotor blade 16
As shown in FIGS. 8 and 9, the output of the sensor 11 is input to the computer 14 via the wiring 13 and the operation signal of the switch 10 of the pilot 9 is input to the computer 14 via the wiring 12, and the computer 14 controls the flight speed of the helicopter 1 and the rotor. The end shape of the rotor blade 16, that is, the sweepback angle, which is optimal for flight conditions such as the number of revolutions
24 is set, and the control command signal is transmitted to the actuator 20, the hydraulic device or the electric motor 21 via the wiring 15 in FIGS. FIG. 3 shows a block diagram of these operations.

In FIG. 1, the case where the sweepback angle 24 occurs at the end of the rotor blade 16 is shown by a solid line, and the case where there is no sweepback angle 24 is shown by a broken line.

The gap between the fixed part 18 and the movable part 17 is provided with a seal 22 made of elastic rubber, synthetic fiber material or the like. According to this embodiment, there is an advantage that the change range of the sweepback angle 24 can be widened.

Next, a second embodiment of the present invention will be described with reference to FIGS. 4 and 5, wherein FIG. 4 is a top view of a rotor blade 25 according to the second embodiment, and FIG. The cross-sectional views of the rotor blade 25 cut at the center along the longitudinal direction are respectively shown as viewed from the rear.

In these figures, the end portion of the rotor blade 25 has a double structure, and includes a movable portion 26 and a fixed portion 27 at the end portion. The movable portion 26 has an actuator 29 and a hydraulic pressure around a rotation center (pin) 28. The rotation or movement 32 is performed by the power of the device or the electric motor 30 so that the retreat angle of the end of the rotor blade 25 can be changed. As shown in FIGS. 8 and 9, the helicopter 1 according to the second embodiment having the rotor blade 25 has an output of the sensor 11 connected to a switch 13 of the pilot 9 through a wiring 13.
10 An operation signal is input to a computer 14 via a wiring 12, and the computer 14 generates a rotor blade optimal for a flight condition such as a flight speed of the helicopter 1 and a rotor speed.
The end shape of 25 is set, and the control command signal is transmitted to the actuator 29, the hydraulic device or the electric motor 30 by the wiring 15 in FIGS. FIG. 3 shows a block diagram of these operations.

In FIG. 4, the case where the sweepback angle occurs at the end of the rotor blade 25 is indicated by a solid line, and the case where there is no sweepback angle is indicated by a broken line.

The gap between the fixed part 27 and the movable part 26 is provided with a seal 31 made of elastic rubber, synthetic fiber material or the like.

Next, a third embodiment of the present invention will be described with reference to FIGS. FIG. 6 is a view of the rotor blade 33 according to the third embodiment as viewed from above, and FIG. 7 is a view of a cross section of the rotor blade 33 of FIG. Shown respectively.

In these figures, the end of the rotor blade 33 has a double structure, and is composed of a movable part 34 and a fixed part 35 at the end, and the movable part 34 is driven by the power of an actuator 36, a hydraulic device or an electric motor 37. , Move 39 to make rotor blade 33
Is configured to be able to change the shape of the end. The helicopter 1 according to the third embodiment having the rotor blades 33 has the eighth and ninth configurations.
As shown in the figure, the output of the sensor 11 is input to a computer 14 via a wiring 13 and the operation signal of the switch 10 of the pilot 9 is input to a computer 14 via a wiring 12. The optimum end shape of the rotor blade 33 is set, and the control command signal is transmitted to the actuator 36, the hydraulic device or the electric motor 37 through the wiring 15 in FIGS. FIG. 3 shows a block diagram of these operations.

The gap between the fixed portion 35 and the movable portion 34 is provided with a seal 38 made of elastic rubber, synthetic fiber material or the like. This embodiment has the advantages of simple structure, small weight and low cost.

As described above, according to the first to third embodiments, the movable portion of the rotor blade is formed into a plane shape optimal for the flight condition at that time by a sensor and a computer via a driving device such as a hydraulic device or an electric motor and an actuator. The advantage is that a helicopter can be obtained which maintains its high performance over all flight conditions.

〔The invention's effect〕

The present invention has the following effects because it is configured as described above.

That is, according to the present invention, the plane shape of the end portion of the rotor blade can be adapted to the optimum condition for the flight condition of the helicopter at that time, so that the helicopter has good performance, efficiency, and economy over the entire flight range. Is obtained.

[Brief description of the drawings]

1 is a top view of a rotor blade according to a first embodiment of the present invention, FIG. 2 is a rear view of a central cross section along the longitudinal direction of the rotor blade of FIG. 1, and FIG. FIG. 4 is an operation block diagram according to first to third embodiments of the present invention, FIG. 4 is a view of a rotor blade according to a second embodiment of the present invention as viewed from above,
FIG. 5 is a view of the central section along the longitudinal direction of the rotor blade of FIG. 4 as viewed from the rear, FIG. 6 is a view of the rotor blade according to the third embodiment of the present invention as viewed from above, and FIG. FIG. 6 is a rear view of a central cross section along the longitudinal direction of the rotor blade of FIG. 6, FIG. 8 is a side view of the helicopter of the first to the first embodiments, and FIG. FIG. 10 is a plan view showing a first example of a conventional rotor blade, FIG. 11 is a plan view showing a second example of the conventional rotor blade, and FIG. FIG. 13 is a plan view showing three examples, and FIG. 13 is a plan view showing a fourth example of a conventional rotor blade. 1 ... helicopter, 3 ... rotating shaft, 4 ... engine, 5 ... fuselage, 6 ... tail rotor, 7 ... vertical tail, 8 ... horizontal tail, 9 ... pilot, 10 ... switch, 11 ... Sensor, 12,13 ... Wiring, 14 ... Computer, 15 ... Wiring, 16 ... Rotor blade, 17 ... Movable part, 18 ... Fixed part, 19 ... Rotation center (pin), 20 ... ... actuator, 21 ... hydraulic device or electric motor, 24 ... retract angle, 25 ... rotor blade, 26 ... movable part, 27 ... fixed part, 28 ... rotation center (pin), 29 ... actuator, 30 …… Hydraulic device or electric motor, 33 …… Rotor blade, 34 …… Movable part, 35 …… Fixed part, 36 …… Actuator, 37 …… Hydraulic device or electric motor.

Claims (1)

(57) [Claims] 1. A rotor blade having a movable part provided at an end so that the plane shape of the end can be changed with respect to a fixed part, a driving means for driving the movable part of the rotor blade, and a driving means for the driving means. A helicopter comprising: a computer for instructing the driving amount of the movable portion; and a sensor for detecting and inputting flight conditions as arithmetic data to the computer.