JP7178099B2 - flying object - Google Patents

Description

TECHNICAL FIELD The present invention relates to an aircraft, and more particularly to an aircraft in which a thrust section and a wing section are connected in a displaceable manner.

Two systems, a so-called tilt-rotor system and a tilt-wing system, are known as aircraft having rotors (rotary wings) and main wings.

Patent Document 1 discloses an aircraft in which the main wing is fixed to the main body, and the entire rotor including the motor is configured to be displaceable in the vertical direction and the flight direction (tilt rotor system).

On the other hand, Patent Document 2 discloses an aircraft in which the main wing and main body are configured to be displaceable in the vertical and flight directions, and the motor and rotor as a whole are fixed to the main wing (tilt wing method).

Japanese Patent Publication No. 2013-501677 Japanese Unexamined Patent Application Publication No. 2017-81360

According to the technique of Patent Document 1, the main wing is in a wide range of the propeller wake when the aircraft is climbing, so the main wing has poor flight efficiency. In addition, the main wing has a negative angle of attack (zero lift angle) at the time of transition from hovering to horizontal flight. That is, there is a danger that the aircraft will descend until the horizontal thrust necessary for generating lift by the main wings is obtained.

According to the technique of Patent Document 2, the entire main wing is displaced, which makes it unstable due to wind resistance.

SUMMARY OF THE INVENTION The present invention has been made in view of the above circumstances, and provides a flying object that enables efficient and safe transition from hovering to level flight.

According to the invention,
a lift generator;
a thrust generator capable of flight and hovering;
a connecting portion displaceably connecting the lift generating portion and the thrust generating portion so that the lift generating portion can maintain a positive angle of attack with respect to the flight direction at least during hovering;
You get an aircraft.

According to the present invention, it is possible to provide a flying object that enables efficient and safe transition from hovering to level flight.

1 is a diagram of an aircraft according to a first embodiment of the present invention; FIG. The illustrated aircraft is in a landing state. It is a figure explaining the flying object concerning a 1st embodiment of the present invention. The illustrated aircraft is in a climb state. It is a figure explaining the flying object concerning a 1st embodiment of the present invention. The illustrated aircraft is in flight in the direction of travel. FIG. 2 is a partially enlarged view showing the vicinity of the lower main wing of the aircraft of FIG. 1; FIG. 2 is a partially enlarged view showing the vicinity of the upper main wing of the aircraft of FIG. 1; FIG. 3 is a partially enlarged view showing the vicinity of the lower main wing of a conventional aircraft. FIG. 3 is a partially enlarged view showing the vicinity of the upper main wing of a conventional aircraft.

The invention according to this embodiment has the following configuration.
[Item 1]
a lift generator;
a thrust generator capable of flight and hovering;
a connecting portion displaceably connecting the lift generating portion and the thrust generating portion so that the lift generating portion can maintain a positive angle of attack with respect to the flight direction at least during hovering;
Airplane.
[Item 2]
The aircraft according to claim 1,
The lift generating section is a wing section,
The thrust generating unit is a rotary blade,
A rotation center axis of the rotor blade and a chord line of the blade portion form a predetermined angle,
The connecting portion connects the lift generating portion and the thrust generating portion so that the predetermined angle can maintain a predetermined range of at least 105 degrees or more and less than 180 degrees at least during takeoff and landing and during hovering.
Airplane.
[Item 3]
The aircraft according to claim 2,
The connection unit connects the lift force generation unit and the thrust force generation unit so that the predetermined angle can be maintained within a predetermined range of 105 degrees or more and 150 degrees or less at least during takeoff, landing, and hovering.
Airplane.
[Item 4]
The aircraft according to any one of claims 1 to 3,
The connecting portion connects the lift generating portion and the thrust generating portion such that the predetermined angle is approximately 180 degrees during flight.
Airplane.

Next, an aircraft according to an embodiment of the present invention will be described with reference to the drawings.

<Structure>
As shown in FIG. 1, the aircraft 1 according to the present embodiment includes an upper main wing 10T and a lower main wing 10B (hereinafter, the upper main wing 10T and the lower main wing 10B are collectively referred to as "main wing 10"). A connecting portion 50 connects the upper main wing 10T and the lower main wing 10B. The connecting portion 50 is connected to a main body portion 60 extending in the front-rear direction and a connecting portion 55 so as to be displaceable. A vertical tail 70 is provided at the rear end of the body portion 60 .

The main wing 10 has a function similar to that of a so-called main wing of an aircraft, and lifts the aircraft 1 by the lift generated on the upper surface of the main wing when traveling in the direction of travel D. As shown in FIG. In the initial state (landing state) shown in FIG. 1, the main wing 10 is oriented with respect to the traveling direction D so that the lift generated when traveling at a positive angle of attack is maximized.

A motor 20T is movably connected to the trailing end (trailing edge) of the upper main wing 10T via a connecting portion 40. As shown in FIG. A propeller 30T is attached to the motor 20T, and the rotation of the motor 20T rotates the propeller 30T to obtain thrust. The motor 20T of the upper main wing 10T according to the present embodiment employs a so-called propulsion type (push type) propulsion method. That is, the pitch of the propeller 30T is adjusted so that when the motor 20T is rotated in the illustrated state, the wind blows downward.

On the other hand, a motor 20B is movably connected to the rear end (trailing edge) of the lower main wing 10B via a connecting portion 40. As shown in FIG. A propeller 30B is attached to the motor 20B, and the propeller 30B is rotated by the rotation of the motor 20B to obtain thrust. The motor 20B of the lower main wing 10B according to the present embodiment employs a so-called traction type (pull type) propulsion method. That is, the pitch of the propeller 30B is adjusted so that the wind blows downward when the motor 20B is rotated in the illustrated state.

In the embodiment described above, the main wing 10 has two main wings, the upper main wing 10T and the lower main wing 10B, but any one of them may be provided. Further, the motors 20T and 20B may be propulsion type (push type), traction type (pull type), or a combination thereof.

As described above, the aircraft according to the present embodiment includes the connecting portion 40 that connects the main wing 10 and the motors 20 (propellers 30B and 30T) so as to be displaceable. Appropriate angles of the main wing 10 and the motor 20 are maintained depending on the situation (the operation of the connecting portion 40 will be described later).

<Flight form>
Hereinafter, the configuration of the aircraft during takeoff, flight and landing according to the present embodiment will be described with reference to FIGS. 1 to 3. FIG.

As shown in FIG. 1, when attempting to climb from the landing state (initial state), the propeller 30B is oriented upward (=the direction in which the propulsive force is generated in the upward direction), and the propeller 30T is oriented downward (=upward). direction).

In addition, both main wings 10 have a positive angle of attack with respect to the direction of travel (that is, the angle between the chord line and the direction of travel is positive, and the direction is forward-rising). When ascending, the motors 20t and 20B are rotated in the illustrated state.

As shown in FIG. 2, during the ascent and hovering of the flying object, the vertical ascent is carried out as it is in the state shown in FIG. At this time, the connecting portion 40 functions so that both main wings 10T and 10B have a positive angle of attack with respect to the traveling direction D.

At this time, a wake is generated by the propeller 30B, but the lower main wing 10B has an angle of attack (an angle that facilitates escape of the wake). That is, when viewed from above, in the portion where the propeller 30B and the lower main wing 10B do not overlap (the portion on the left side of the axis Ax in FIG. 4(a)), the wake flows downward as it is, while the propeller In the portion where 30B and lower main wing 10B overlap (the portion on the right side of axis Ax in FIG. 4A), the wake flows downward along the upper surface of lower main wing 30T.

By the way, in the case of a conventional tilt-rotor type flying object, it starts to climb in the initial state shown in FIGS. In addition, it is necessary to displace the motor 20 slowly while maintaining the angle of attack of the main wing 10B' and the main wing 10T' at 0 degrees so that the main wing 10B' and the main wing 10T' do not have a negative angle of attack (zero lift angle). be. If the motor 20 is displaced quickly, for example, as shown in FIGS. causes a temporary descent, and is also the cause of the crash.

According to the embodiment of the present invention, as shown in FIG. 4(b), since the hovering has a positive angle of attack, even when the displacement of the motor 20 starts and the body moves in the traveling direction, , it is possible to maintain a sufficient angle of attack to obtain lift, so that it can safely transition to level flight without changing altitude.

As shown in FIG. 3, when the transition from hovering to level flight is completed, propeller 30B faces forward and propeller 30T faces rearward. By orienting the propellers 30B and 30T in the horizontal direction, forward propulsion can be obtained.

It should be noted that when the robot reaches the destination above the ground, it is displaced to the same attitude as in FIG. 2 in order to perform hovering again. Then, in that state, descend and land.

<Details of displacement>
4-7, the details of the transition from hovering to level flight (at the time of ascent and) will now be described.

FIG. 4(a) shows the vicinity of the lower main wing 10B in the hovering state. As shown in the figure, the rotation center axis Ax of the propeller 30B and the chord line Wx of the main wing 10B form a predetermined angle θ. During hovering, the predetermined angle θ may be in a predetermined range of 105 degrees or more and less than 180 degrees. is desirable.

As shown in FIG. 4(b), when the hovering state is shifted to the horizontal flight state, the connecting portion 40 is displaced so that the motor 20 is tilted forward and at the same time the main wing 10B is parallel to the horizontal direction. is displaced to

As shown in FIG. 4(c), when the transition to the horizontal flight state is completed, the central axis of the propeller 30B becomes parallel to the horizontal direction.

Similarly, FIG. 5(a) shows the vicinity of the upper main wing 10T in a hovering state. As shown in the figure, the rotation center axis Ax of the propeller 30B and the chord line Wx of the main wing 10B form a predetermined angle θ. During hovering, the predetermined angle θ may be in a predetermined range of 105 degrees or more and less than 180 degrees. is desirable.

As shown in FIG. 5(b), when the hovering state is shifted to the horizontal flight state, the connecting part 40 is displaced and the motor 20 is tilted forward, and at the same time the upper main wing 10T becomes parallel to the horizontal direction. is displaced as follows.

As shown in FIG. 5(c), when the transition to the horizontal flight state is completed, the central axis of the propeller 30T becomes parallel to the horizontal direction (that is, the central axis Ax and the chord line are 180 degrees). .

1 Aircraft 10 Main Wing 10B Lower Wing 10T Upper Wing 20 Motor 30 Propeller 30B Lower Propeller 30T Upper Propeller 40 Connecting Part 50 Connecting Part 60 Main Body 70 Vertical Tail

Claims (4)

a main wing ;
a plurality of rotor blades capable of at least ascent and horizontal flight ,
the main wing has a positive angle of attack with respect to the flight direction at least when climbing ;
The plurality of rotor blades are provided at least one each in front and rear of the main wing,
Airplane. The aircraft according to claim 1 ,
The rotor blades are rotatable in the flight direction, and when the flight direction is set to 0 degrees of the rotation angle of the rotor blades,
The rotation range of the rotor blade when attached to the front is from 0 degrees to an angle obtained by subtracting the angle of attack from 90 degrees,
The rotation range of the rotor when mounted rearward is from 180 degrees to 270 degrees minus the angle of attack.
An aircraft characterized by : The aircraft according to any one of claims 1 and 2 ,
The main wing maintains the positive angle of attack with respect to the flight direction for a predetermined time after the start of transition from climb to level flight.
Airplane. The aircraft according to any one of claims 1 to 3 is a vertical take-off and landing aircraft,
An aircraft characterized by:

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