JPH04260895A - Helicopter - Google Patents

Abstract

PURPOSE:To provide a helicopter with emergency wings enabling safe landing onto the ground or the water surface without causing the crash of the helicopter even in the case of the main rotor or the like of the helicopter being blown off. CONSTITUTION:Movable emergency wings 11 are provided laterally at a body, below the main rotor of a single rotor type helicopter. These movable emergency wings 11 are protruded laterally from the body by the switching operation of a pilot to generate lift, and enclosed into the body at the non-emergency time to reduce air resistance.

Description

[Detailed description of the invention]

0001

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a helicopter with emergency wings.

0002

2. Description of the Related Art As shown in FIG. 20, a helicopter 1 rotates a rotating shaft 3 using the power of an engine 4, rotates a main rotor 2 attached to the rotating shaft 3, and obtains upward lift. At the same time as supporting the weight of the helicopter 1, the main rotor 2 generates thrust to move the helicopter 1 forward.

In a conventional helicopter, when the engine 4 fails and the main rotor 2 cannot be rotated normally, the main rotor 2 is automatically rotated (autorotation) as shown in FIG. 1 was landing (if on the ground) or in water (if horizontal).

[0004] However, if the main rotor 2 of the helicopter blows away, or if the attachment part of the main rotor 2 breaks down as shown in Figs. 23 and 24, and the main rotor 2 cannot rotate, , as shown in FIG. 25, the helicopter crashes, collides with the ground or water surface, and is destroyed, resulting in the deaths of the passengers and others.

[0005]

[Problems to be Solved by the Invention] As mentioned above, in conventional helicopters, when the engine 4 fails and the main rotor 2 cannot be rotated normally, the main rotor 2 is rotated as shown in FIG. By automatically rotating (autorotating) the helicopter 2, the helicopter was allowed to glide and land or land at an appropriate position on the ground or water surface. The trajectory of the helicopter at that time is as shown in the helicopter path 50.

[0006] For some reason, the main rotor 2 may be blown off, resulting in a helicopter 54 without a main rotor as shown in FIG. 23, or a helicopter 57 without a main rotor and rotating shaft as shown in FIG. If the attachment part of the main rotor 2 fails and the main rotor 2 becomes unable to rotate, as shown in FIG. 25 (FIG. 25 shows the case of a helicopter 54 without a main rotor), the helicopter Since there is no way to support the weight, the helicopter has no choice but to crash, causing the helicopter to crash into the ground or water, destroying the helicopter and killing its occupants.

[0007] The present invention solves the above-mentioned problems of conventional helicopters, and prevents the helicopter from falling into an emergency situation where the main rotor blows out or the main rotor attachment part breaks down and the main rotor cannot rotate. The purpose of the present invention is to provide a helicopter that can safely land or land on the ground or water surface even in the event of a collision.

[0008]

[Means for solving the problem] (First means)

000
9] The helicopter according to the present invention is a single-rotor type helicopter, and includes emergency wings that are movable to the left and right sides of the body below the main rotor, and includes a switch for operating the emergency wings, a drive source, and an actuator. In an emergency, the emergency wing is activated by the pilot's switch operation.
It is characterized by protruding or deploying to the left and right sides of the fuselage, and being stored within the fuselage in non-emergency situations. (Second means)

[0010] In a first aspect, the helicopter according to the present invention includes movable emergency wings provided on the left and right sides of the fuselage below the main rotor, a sensor provided at the attachment portion between the main rotor and the rotating shaft, and a computer. The computer inputs the signal from the sensor, outputs a control signal to the emergency wing drive source and actuator, and automatically protrudes or deploys the emergency wing to the left and right of the fuselage in an emergency. .

[0011]

[Operation] If the helicopter is in an emergency situation,
The emergency wing 11 shown in FIG. 3, the emergency wing 17 shown in FIG. 3, the emergency wing 20 shown in FIG. 4, and the emergency wing 22 shown in FIG. The emergency wings 34 shown in FIG. 1 are deployed on both sides of the helicopter fuselage 5. Therefore, it is the same as a helicopter being equipped with the main wings of a fixed-wing aircraft, and these emergency wings 11, 1
Air force (lifting force) as shown in FIG. 19 is activated at 7, 20, 22, 29, and 34, and the weight of the helicopter can be supported by this lifting force. Therefore, the helicopter can glide, and the helicopter can safely land or land on the ground or water surface.

These emergency wings 11, 17, 20, 22,
The larger the sizes of 29 and 34 are when viewed from above (the larger the area of the emergency wing on the outside of the helicopter's fuselage 5).
The aerodynamic force that supports the weight of a helicopter is large. The vertical positions of the emergency wings 11, 17, 20, 22 with respect to the fuselage 5 are shown in Figs.
As shown in Figure 8, it may be in any of the upper, middle, and lower positions;
As shown in FIGS. 9 and 10, the number of emergency wings 25, 27 may be two or three. The greater the number, the greater the effect.

When the pilot 9 operates the switch 10, an electrical signal is transmitted to the drive source 13 through the wiring 14.
emergency wing 11 via actuators 12, 23, 30;
17, 20, 22, 25, 27, 29, and 34 can be moved to protrude or unfold on both sides of the helicopter body 5. As the drive source 13, hydraulic pressure, pneumatic pressure, electric motor, spring, etc. are used, so the emergency wing 1 can be reliably activated.
1, 17, 20, 22, 29, and 34 can be moved to protrude or unfold on both sides of the helicopter body 5.

According to the computer-controlled method using the computer 40 shown in FIG. 14, the pilot does not have to perform any operations, which reduces the pilot's workload, and when the helicopter falls into an emergency situation,
emergency wing 11 by automatic computer control;
17, 20, 22, 29, and 34 can be moved to protrude or unfold on both sides of the helicopter body 5.

[0015]

Embodiment A first embodiment of the present invention is shown in FIGS. 1 and 2.

FIG. 1 is a top view of the first embodiment, and FIG.
shows an operational block diagram of the first embodiment. As shown in FIG. 1, the emergency wings 11 are protruded from both left and right sides of the helicopter body 5 in an emergency, and are housed in the helicopter body 5 in a stowed state 16 in non-emergency situations. The main rotor 2 of the helicopter is blown away, the main rotor 2 and the rotating shaft 3
In an emergency situation, such as when the main rotor 2 blows out or the main rotor 2 is unable to rotate due to a failure in the attachment part of the main rotor 2, when the pilot 9 operates the switch 10, an electrical signal is sent through the wiring 14. is transmitted to the drive source 13, the drive source 13 is operated, and the emergency wing 11 is moved and projected to the left and right outer sides of the fuselage 5 of the helicopter via the actuator 12, thereby forming the emergency wing 11. A block diagram of these operations is shown in FIG. As the drive source 13, hydraulic pressure, pneumatic pressure, an electric motor, a spring, etc. are used.

When the emergency wings 11 are formed on both the left and right sides of the helicopter's fuselage 5 in this way, they act in the same way as the main wings of a fixed-wing aircraft, and the emergency wings receive aerodynamic force (lifting force) that lifts the helicopter upward. ), the helicopter can glide without crashing and safely land or land at an appropriate location on the ground or water surface. The vertical position of the emergency wing 11 with respect to the fuselage 5 of the helicopter may be any of the upper, middle, and lower positions of the fuselage 5, as shown in FIGS. 6 to 8. The first embodiment can be applied to any of the fifth, sixth, and ninth embodiments. A second embodiment of the invention is shown in FIGS. 3 and 2.

FIG. 3 is a top view of the second embodiment, FIG.
shows an operational block diagram of the second embodiment. As shown in FIG. 3, the emergency wings 17 are protruded from both left and right sides of the helicopter fuselage 5 in an emergency, and are stored in the helicopter fuselage 5 as an emergency wing stowed state 19 in non-emergency situations. In an emergency situation where the main rotor 2 of the helicopter is blown away, the main rotor 2 and the rotating shaft 3 are blown off, or the attachment part of the main rotor 2 is broken and the main rotor 2 cannot rotate. When the pilot 9 operates the switch 10, an electric signal is transmitted to the drive source 13 through the wiring 14, the drive source 13 is activated, and the emergency wings 17 are moved to the left and right sides of the helicopter's fuselage 5 via the actuator 12. It moves outward on both sides about the rotation center 18 and is expanded to form the emergency wings 11. A block diagram of these operations is shown in FIG. As the drive source 13, hydraulic pressure, pneumatic pressure, an electric motor, a spring, etc. are used.

When the emergency wings 17 are formed on both the left and right sides of the helicopter fuselage 5 in this way, they act in the same way as the main wings of a fixed-wing aircraft, creating an aerodynamic force (lifting force) that lifts the helicopter upward. This allows the helicopter to glide without crashing and safely land or land at an appropriate location on the ground or water surface. The vertical position of the emergency wing 17 with respect to the helicopter fuselage 5 is shown in FIGS. 6 to 8.
As shown in the figure, it may be placed at any of the upper, middle, and lower positions of the body 5. As the second embodiment, a third embodiment of the present invention which can be applied to any of the fifth, sixth and ninth embodiments is shown in FIGS. 4 and 2.

FIG. 4 is a top view of the third embodiment, and FIG.
shows an operational block diagram of the third embodiment. As shown in FIG. 4, the emergency wings 20 are protruded from both left and right sides of the helicopter fuselage 5 in an emergency, and are stored in the helicopter fuselage 5 in an emergency wing stowed state 21 in non-emergency situations. In an emergency situation where the main rotor 2 of the helicopter is blown away, the main rotor 2 and the rotating shaft 3 are blown off, or the attachment part of the main rotor 2 is broken and the main rotor 2 cannot rotate. When the pilot 9 operates the switch 10, an electric signal is transmitted to the drive source 13 through the wiring 14, the drive source 13 is activated, and the emergency wings 20 are moved to the left and right sides of the helicopter fuselage 5 via the actuator 12. It moves outward on both sides about the rotation center 18 and is expanded to form an emergency wing 20. A block diagram of these operations is shown in FIG. As the drive source 13, hydraulic pressure, pneumatic pressure, an electric motor, a spring, etc. are used.

[0021] When the emergency wings 20 are formed on the outside of the left and right sides of the helicopter fuselage 5 in this way, they act in the same way as the main wings of a fixed-wing aircraft, giving them an aerodynamic force (lifting force) that lifts the helicopter upward. ), the helicopter can glide without crashing and safely land or land at an appropriate location on the ground or water surface. The vertical position of the emergency wing 20 with respect to the helicopter fuselage 5 is shown in FIGS.
As shown in FIG. 8, it may be placed at any of the upper, middle, and lower positions of the body 5. This third embodiment can be applied to any of the fifth, sixth, and ninth embodiments. The planar shape (outside portion of the fuselage 5) of the emergency wing 20 of this third embodiment is reversed from the front and back of the second embodiment. Fourth aspect of the present invention
Examples are shown in FIGS. 5 and 2.

FIG. 5 is a top view of the fourth embodiment, and FIG.
shows an operational block diagram of the fourth embodiment. As shown in FIG. 5, the emergency wings 22 are protruded from both left and right sides of the helicopter fuselage 5 in an emergency, and are stored in the helicopter fuselage 5 in an emergency wing stowed state 24 in non-emergency situations. In an emergency situation where the main rotor 2 of the helicopter is blown away, the main rotor 2 and the rotating shaft 3 are blown off, or the attachment part of the main rotor 2 is broken and the main rotor 2 cannot rotate. When the pilot 9 operates the switch 10, an electric signal is transmitted to the drive source 13 through the wiring 14, the drive source 13 is activated, and the emergency wings 22 are moved to the left and right sides of the helicopter fuselage 5 via the actuator 23. It moves outward on both sides around the rotation center 18 and is expanded to form an emergency wing 22. A block diagram of these operations is shown in FIG. As the drive source 13, hydraulic pressure, pneumatic pressure, an electric motor, a spring, etc. are used.

[0023] When the emergency wings 22 are formed on both the left and right sides of the helicopter's fuselage 5 in this way, they act in the same way as the main wings of a fixed-wing aircraft, creating an aerodynamic force (lifting force) that lifts the helicopter upward. This allows the helicopter to glide without crashing and safely land or land at an appropriate location on the ground or water surface. The vertical position of the emergency wing 22 relative to the fuselage 5 of the helicopter may be any of the upper, middle, and lower positions of the fuselage 5, as shown in FIGS. 6 to 8. The fourth embodiment can be applied to any of the fifth, sixth, and ninth embodiments. The fourth embodiment is a combination of the second and third embodiments described above, and is a combination of the second and third embodiments described above.
The effect is greater than that of the embodiment or the third embodiment alone. FIG. 9 shows a rear view of the fifth embodiment of the present invention.

Emergency wings 11, 1 of the first to fourth embodiments described above
7, 20, 22 form a pair of emergency wings on both left and right sides of the fuselage 5 of the helicopter, but in the fifth embodiment, two pairs of emergency wings 25 are formed.
(There are two stages of emergency wings in the vertical direction of the fuselage 5. They may be positioned in any position.) The emergency wings 25 are protruded from both left and right sides of the helicopter fuselage 5 in an emergency.
If it is not an emergency, the wing is stored in the fuselage 5 of the helicopter in an emergency wing storage state 26. In an emergency situation where the main rotor 2 of the helicopter is blown away, the main rotor 2 and the rotating shaft 3 are blown off, or the attachment part of the main rotor 2 is broken and the main rotor 2 cannot rotate. is the first
- It operates in the same manner as the fourth embodiment, that is, according to the operation block diagram shown in FIG. The fifth embodiment is the first embodiment described above.
This can be applied to any of the embodiments 1 to 4, and can also be applied to the ninth embodiment. The effect of the fifth embodiment is greater than that of the pair of emergency wings 11, 17, 20, 22 shown in the first to fourth embodiments. FIG. 10 is a rear view of the sixth embodiment of the present invention.
Shown below.

Emergency wings 11, 1 of the first to fourth embodiments described above
7, 20, and 22 form a pair of emergency wings on both left and right sides of the fuselage 5 of the helicopter, but in the sixth embodiment, three pairs of emergency wings 27 (three stages of emergency wings in the vertical direction of the fuselage 5) are formed. (The position can be any position.)

As shown in FIG. 10, the emergency wings 27 are protruded from both left and right sides of the helicopter fuselage 5 in an emergency, and are stored in the helicopter fuselage 5 in an emergency wing stowed state 28 in non-emergency situations. If the main rotor 2 of the helicopter blows off, or the main rotor 2 and the rotating shaft 3 blow off,
In an emergency such as when the main rotor 2 attachment part breaks down and the main rotor 2 cannot rotate, the first to fourth
It operates in the same manner as the embodiment, ie, according to the operational block diagram shown in FIG.

The sixth embodiment can be applied to any of the first to fourth embodiments described above, and can also be applied to the ninth embodiment. The effect of the sixth embodiment is greater than that of the pair of emergency wings 11, 17, 20, 22 shown in the first to fourth embodiments and the two pairs of emergency wings 25 shown in the fifth embodiment. If there is space on the sides of the fuselage 5 of the helicopter, three pairs of emergency wings 27 shown in the sixth embodiment are provided.
In addition, four or more pairs of emergency wings may be used. FIG. 11 shows a rear view of the seventh embodiment of the present invention.

As shown in FIG. 11(a), in an emergency, the emergency wings 29 are moved to the left and right sides of the helicopter's fuselage 5 and deployed, and in non-emergency situations, they are stored in the helicopter's fuselage 5 as an emergency wing stowed state 33. It will be stored. If the main rotor 2 of the helicopter blows off, the main rotor 2 and the rotating shaft 3 blow off, or the attachment part of the main rotor 2 breaks down, the main rotor 2
In an emergency situation where the machine cannot rotate,
When the pilot 9 operates the switch 10, an electric signal is transmitted to the drive source 13 through the wiring 14, the drive source 13 is activated, and the emergency wings 29 are activated via the actuator 30 on both the left and right sides of the helicopter's fuselage 5. It moves outward around the hinge 31 and unfolds to form the emergency wing 27. A block diagram of these operations is shown in FIG. Drive source 1
As for 3, hydraulic pressure, pneumatic pressure, electric motor, spring, etc. are used.

In this way, when the emergency wings 29 are formed on the outside of the left and right sides of the helicopter fuselage 5, they act in the same way as the main wings of a fixed-wing aircraft, giving them an aerodynamic force (lifting force) that lifts the helicopter upward. ), the helicopter can glide without crashing and safely land or land at an appropriate location on the ground or water surface. The above explanation has been about the emergency wing 29 for the bulky fuselage 5, but the emergency wing 58 shown in FIG. 11(b) for the rounded fuselage 5
The same applies to . The seventh embodiment can also be applied to the ninth embodiment. FIG. 12 shows a rear view of the eighth embodiment of the present invention.

As shown in FIG. 12(a), in an emergency, the emergency wings 34 are moved to the left and right sides of the helicopter's fuselage 5 and deployed, and in non-emergency situations, the emergency wings are stored in the helicopter's fuselage 5. It is stored as 35. In an emergency situation where the main rotor 2 of the helicopter is blown away, the main rotor 2 and the rotating shaft 3 are blown off, or the attachment part of the main rotor 2 is broken and the main rotor 2 cannot rotate. When pilot 9 operates switch 10, wiring 1
4, the electrical signal is transmitted to the drive source 13, and the drive source 1
3 is activated, the emergency wing 2 is activated via the actuator 30.
9 is a hinge 31 on the outside of both left and right sides of the helicopter fuselage 5.
and expands to form an emergency wing 34. A block diagram of these operations is shown in FIG. As the drive source 13, hydraulic pressure, pneumatic pressure, an electric motor, a spring, etc. are used.

[0031] When the emergency wings 34 are formed on the outside of the left and right sides of the helicopter fuselage 5 in this way, they act in the same way as the main wings of a fixed-wing aircraft, giving them an aerodynamic force (lifting force) that lifts the helicopter upward. ), the helicopter can glide without crashing and safely land or land at an appropriate location on the ground or water surface.

While the seventh embodiment deploys the emergency wing 29 upward, the eighth embodiment deploys the emergency wing 34 downward. As shown in FIG. 13, the lower surface of the fuselage 5 and the emergency wing 34 create a large flat surface on the lower side, so when the helicopter lands on the water surface 36, the sinking speed of the helicopter is lower than in the case of sinking as shown in FIG. This is advantageous in terms of safety because it has a damping effect against lateral vibration. Although the above explanation was about the emergency wing 34 for the curvy fuselage 5, the same applies to the emergency wing 60 shown in FIG. 12(b) for the rounded fuselage 5. The eighth embodiment can also be applied to the ninth embodiment. FIG. 14 shows a ninth embodiment of the present invention.
~ Shown in Figure 15. FIG. 14 is a rear view of the ninth embodiment, and FIG. 15 is an operational block diagram of the ninth embodiment.

In the first to eighth embodiments described above, the emergency wings 11, 17, 20, 22, 25, 27, 29
, 34 is operated by a switch operation by the pilot 9, which increases the workload of the pilot 9. In order to improve this, the ninth embodiment employs a control method using a computer 40, and the emergency wings 11,
The protruding or unfolding operations of 17, 20, 22, 25, 27, 29, and 34 are automatically performed. Therefore, Figure 14
As shown in FIG. 3, a sensor 38 is installed at the attachment part of the main rotor 2 and the rotating shaft 3, and this sensor detects whether the main rotor 2 is blown or the main rotor 2 and the rotating shaft 3 are blown. It is detected that the attachment part of the main rotor 2 suddenly breaks down and the main rotor 2 cannot rotate, and an electrical signal is input to the computer 40 via the wiring 39.
The control signal of
1. Move 17, 20, 22, 25, 27, 29, 34 to protrude or deploy on both sides of the helicopter body 5.

According to the ninth embodiment, there is no need for the pilot 9 to operate directly, which can reduce the workload of the pilot 9, and since the operation is controlled by a computer, the operation is reliable and the flight safety of the helicopter is improved. It becomes possible to ensure security.

[0035]

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

(1) In an emergency situation where the main rotor of the helicopter is blown off, the main rotor and the rotating shaft are blown off, or the main rotor attachment part is broken and the main rotor cannot rotate. Even in a helicopter, the pilot can operate a switch to protrude or deploy the emergency wing to act like the main wing of a fixed-wing aircraft, generating aerodynamic force (lift) that lifts the helicopter upward. Therefore, the helicopter can glide and safely land or land at an appropriate location on the ground or water surface, and safety can be greatly improved.

(2) By having a sensor and a computer installed at the attachment point between the main rotor and the rotating shaft, the emergency wing can be automatically protruded or deployed without the pilot 9 operating a switch. As a result, the pilot's workload can be significantly reduced, and since the system is operated automatically and reliably, it can also contribute to ensuring flight safety.

[Brief explanation of the drawing]

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

FIG. 2 is an operational block diagram of first to eighth embodiments of the present invention.

FIG. 3 is a top view of a second embodiment of the present invention.

FIG. 4 is a top view of a third embodiment of the present invention.

FIG. 5 is a top view of the fourth embodiment of the present invention.

FIG. 6: Emergency wing mounting positions of the first to fourth embodiments of the present invention (
Diagram showing the middle airfoil.

FIG. 7: Emergency wing attachment positions of the first to fourth embodiments of the present invention (
A diagram showing a low wing type).

FIG. 8: Emergency wing mounting positions of the first to fourth embodiments of the present invention (
A diagram showing a high wing type).

FIG. 9 is a rear view of the fifth embodiment of the present invention.

FIG. 10 is a rear view of the sixth embodiment of the present invention.

FIG. 11 is a rear view of the seventh embodiment of the present invention.

FIG. 12 is a rear view of the eighth embodiment of the present invention.

FIG. 13 is a diagram showing a helicopter floating on the water surface.

FIG. 14 is a rear view of the ninth embodiment of the present invention.

FIG. 15 is an operational block diagram of a ninth embodiment of the present invention.

FIG. 16 is a diagram showing the lift force when the main rotor rotates normally.

FIG. 17 is a diagram showing the lift force when the main rotor is idling.

FIG. 18 is a diagram showing lift force without a main rotor.

FIG. 19 is a diagram showing the lift force when the present invention is equipped with an emergency wing.

FIG. 20 is a diagram illustrating the entire helicopter.

FIG. 21 is a diagram showing a flight path when a helicopter malfunctions.

FIG. 22 is a diagram showing how the helicopter sinks into the water.

FIG. 23 is a diagram showing a state in which the main rotor of the helicopter is missing.

FIG. 24 is a diagram showing a state in which the main rotor and rotating shaft of the helicopter are missing.

FIG. 25 is a diagram showing a helicopter crash.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 1... Helicopter, 2... Main rotor, 3... Rotating shaft, 4... Engine, 5... Fuselage, 6... Horizontal stabilizer, 7... Vertical stabilizer, 8... Tail rotor, 9... Pilot, 10... Switch, 11...
emergency wing, 12... actuator, 13... drive source, 14...
Wiring, 16...Emergency wing stowed state, 17...Emergency wing, 18...Rotation center, 19...Emergency wing stowed state, 20...Emergency wing, 21...
Emergency wing stowed state, 22... Emergency wing, 23... Actuator, 24... Emergency wing stowed state, 25... Emergency wing, 26... Emergency wing stowed state, 27... Emergency wing, 28... Emergency wing stowed state, 29
...Emergency wing, 30...Actuator, 31...Hinge, 33
...Emergency wing stowed state, 34...Emergency wing, 35...Emergency wing stowed state, 36...Water surface, 38...Sensor, 39...Wiring, 40...Computer, 41...Wiring, 42...Lift force by main rotor (
44... Lift force by the main rotor (small), 47... Lift force by the main rotor (none), 48... Lift force acting on the emergency wing,
50... Helicopter path, 54... Helicopter without main rotor, 57... Helicopter without main rotor and rotating shaft, 5
8...Emergency wing, 59...Hinge, 60...Emergency wing.

Claims (2)

[Claims] 1. A single rotor type helicopter, wherein an emergency wing is provided which is movable to the left and right of the fuselage below the main rotor, and a switch for operating the emergency wing;
1. A helicopter comprising a drive source and an actuator, wherein the emergency wings are protruded or deployed to the left and right sides of the fuselage by a pilot's switch operation in an emergency, and are housed within the fuselage in a non-emergency. 2. A single rotor type helicopter, comprising: movable emergency wings provided on the left and right sides of the fuselage below the main rotor; a sensor provided at the attachment portion between the main rotor and the rotating shaft; and a computer; A helicopter, wherein a computer inputs a signal from the sensor, outputs a control signal to an emergency wing drive source and an actuator, and automatically protrudes or deploys the emergency wing to the left and right of the fuselage in an emergency.