JP2019206199A - Air vehicle - Google Patents

Abstract

To provide an air vehicle which can launch or take off vertically and achieves reduction of wind pressure immediately below the air vehicle.SOLUTION: An air vehicle 1 includes: a jet engine 13 which jets jet blast in a vertically downward direction; a nozzle 14 having a nozzle suction port 141 for suctioning the jet blast and a nozzle exhaust port 142 oriented in a horizontal direction; and a blade 11 disposed at the outer side of the nozzle exhaust port 142. Further, the nozzle 14 generally has a conical shape. The nozzle suction port 141 opens oriented in a vertically upward direction near a peak of the conical shape. The nozzle exhaust port 142 opens in a ring shape in all outer directions on a bottom surface circumferential of the conical shape.SELECTED DRAWING: Figure 1

Description

  The present invention relates to an aircraft.

  Conventionally, various aircraft are used to transport human cargo. Among these aircraft, aircraft that can take off and land vertically, such as helicopters, are highly convenient because they do not require long runways, and are widely used especially in disasters. Recently, drones, which are unmanned aircraft operated remotely, are attracting attention.

  Patent Document 1 discloses that a plurality of inner rotor units (RU11 to RU14) disposed on a first circumference separated by a predetermined distance from the center of the airframe are separated from the center of the airframe by a predetermined distance larger than the predetermined distance. In a vertical take-off and landing vehicle including a plurality of outer rotor units (RU21 to RU24) arranged on the second circumference and a control means for driving and controlling the inner rotor unit and the outer rotor unit, Discloses an aircraft that is mainly operated by operating the inner rotor units (RU11 to RU14), and the attitude control of the fuselage is mainly performed by operating the outer rotor units (RU21 to RU24).

JP2014-240242

  In an aircraft that can take off and land vertically as described above, especially in a size that can carry a person, the wind pressure directly below the aircraft is considerably large at a position close to the ground. For this reason, it is difficult for people to approach and work directly under the aircraft close to the ground, or when the baggage to be transported or transported is placed directly under the aircraft, There was a fear of being skipped.

  The present disclosure has been made in view of the above-described circumstances, and an object thereof is to provide an aircraft that can take off and land vertically with reduced wind pressure immediately below the aircraft.

  An aircraft according to the present disclosure includes a jet engine that jets a jet jet vertically downward, a nozzle inlet that sucks the jet jet, and a nozzle that has a nozzle outlet that faces in a horizontal direction, and is disposed outside the nozzle outlet. And an wing that is provided with a wing.

  Further, in the aircraft according to the present disclosure, the nozzle has a conical shape as a whole, the nozzle intake port opens vertically near the apex of the cone shape, and the nozzle exhaust port has the conical shape. You may open in a ring shape in the outer omni direction along the circumference of the bottom face. The nozzle may have a current plate near the nozzle exhaust port.

  In the aircraft according to the present disclosure, the wing may have a ring shape that is disposed outside the nozzle exhaust port. Moreover, the said wing | blade may operate | move so that the angle of a rear edge part may be changed, and may have several ladder arrange | positioned on the circumference. The wing may further include a rotation suppression ladder that extends vertically to the upper surface and changes an angle on the upper surface with reference to an arrangement position of the upper surface.

  In the aircraft according to the present disclosure, a payload mounting portion may be further provided below the nozzle. In addition, the apparatus may further include a separation operation unit that performs an operation of separating the payload mounting unit, and the payload mounting unit may include a parachute that operates when the payload mounting unit is separated by the separation operation.

  In addition, the aircraft according to the present disclosure may further include a cockpit in which a maneuvering unit that performs at least a jet engine control instruction is disposed around the jet engine.

  With the configuration as described above, the aircraft of the present disclosure can take off and land vertically, and the wind pressure directly under the aircraft can be reduced.

1 is a plan view of an aircraft of the present disclosure. FIG. 2 is a partial cross-sectional view showing a side surface of the aircraft of FIG. 1. It is a fragmentary sectional view shown about the example of the side surface of a payload mounting part. It is a side view shown about an aircraft when a payload mounting part is connected.

  Hereinafter, the configuration and function of the aircraft of the present disclosure will be described with reference to the drawings. In the description, similar elements are denoted by the same reference numerals, and redundant description is omitted as appropriate.

  FIG. 1 is a plan view of an aircraft 1 according to the present invention. FIG. 2 is a partial cross-sectional view showing a side surface of the aircraft 1 of FIG. As shown in these drawings, the aircraft 1 includes a jet engine 13, a nozzle 14, and a wing 11.

  The jet engine 13 compresses the air sucked from the intake port of the jet engine 13, discharges the expanded air by igniting with the fuel, and jets a jet jet, and further rotates the turbine to take in the air from the intake port. Of the mechanism. In the jet engine 13 of the present disclosure, the jet jet is arranged so as to be ejected vertically downward. As the jet engine 13, a publicly known one can be used, and for example, one that has been reduced in weight by a ceramic composite material or the like can be used. Moreover, it is good also as using various lightweight materials, such as carbon. The nozzle 14 has a nozzle intake port 141 for intake of a jet jet ejected from the jet engine 13 and a nozzle exhaust port 142 directed in the horizontal direction. The nozzle inlet 141 may be disposed so as to close the jet outlet of the jet engine 13. The blade 11 is disposed outside the nozzle exhaust port 142.

  Here, the nozzle 14 may have a conical shape as a whole. In this case, the nozzle intake port 141 opens vertically upward near the apex of the conical shape, and the nozzle exhaust port 142 opens in a ring shape in all outer directions along the circumference of the conical bottom surface. . The nozzle 14 is formed of a substantially conical outer nozzle wall 144 and a substantially conical inner nozzle wall 145 housed inside the outer nozzle wall 144, and faces the outer nozzle wall 144 vertically upward. An opening is formed and the top of the inner nozzle wall 145 is closed. The outer nozzle wall portion 144 and the inner nozzle wall portion 145 are each formed with side surfaces that are convex toward the inner side, and thereby the jet jet jetted vertically downward can be smoothly changed in the horizontal direction. The outer nozzle wall 144 and the inner nozzle wall 145 may be connected by a rib (not shown) or the like.

  The exhaust angle of the nozzle exhaust port 142 can be ± 10 ° from the horizontal direction, more preferably ± 5 °. Thereby, the wind pressure directly under the aircraft 1 can be reduced. The nozzle 14 may further include a rectifying plate 143 near the nozzle exhaust port 142. Thereby, the air exhausted from the nozzle 14 can be ejected to the blade 11 without being disturbed.

  The blade 11 has a ring shape disposed outside the nozzle exhaust port 142, and is a blade having the nozzle exhaust port 142 side as a leading edge and the outer peripheral side as a trailing edge. The wing | blade 11 has the several ladder 111 which operate | moves so that the angle of a rear edge part may be changed. Although the number of ladders 111 is six in the drawing, the number of ladders 111 can be a plurality other than six.

  The wing 11 may further include a rotation suppression ladder 113 that extends vertically upward on the upper surface of the wing 11 and changes an angle on the upper surface with respect to one point of the position of the upper surface. For example, the rotation suppression ladder 113 can move by changing the angle as indicated by an arrow 91 in FIG. The rotation suppression ladder 113 receives the air flow exhausted from the nozzle exhaust port 142 on the upper surface of the blade 11 and bends it to change the circumferential direction component into an air flow. As a result, for example, the rotational moment received by the blades 11 and others caused by the rotation of the turbine blades of the jet engine 13 is canceled, and the blades 11 and other parts connected to the jet engine 13 are prevented from rotating (spinning). Can do. The rotation suppression ladder 113 of the present disclosure is formed in a shape that is continuous with the support column 112 that connects the jet engine 13 and the blades 11, but may not have such a configuration.

  As described above, the air 31 is sucked into the jet engine 13, jetted as a jet flow vertically downward from the jet engine 13, bent by the nozzle 14 to become a horizontal flow, and blown to the leading edge of the blade 11. Thereby, lift is generated in the wing 11 and the aircraft 1 can be lifted vertically. The lift can be adjusted by the output of the jet engine 13 and the angle of the ladder 111. Further, the horizontal movement can be performed by making the angles of the plurality of ladders 111 different. The rotation of the aircraft 1 can be suppressed by the angle of the rotation suppression ladder 113. With such a configuration, in the aircraft 1 of the present disclosure, it is possible to take off and land vertically, and since air is not blown directly under the aircraft 1, the wind pressure directly under the aircraft 1 can be reduced. In the present embodiment, the nozzle shape is as described above. However, the nozzle shape is not limited to this, and other nozzle shapes that generate a lift by blowing a jet jet to the front edge of the blade 11 may be used.

Further, the aircraft 1 may further include a cockpit 12 around the jet engine 13 in which a steering operation unit 123 that instructs at least control of the jet engine 13 is disposed. The cockpit 12 has a window 122, and the steering operation unit 123 may control the ladder 111 and the rotation suppression ladder 113 in addition to the jet engine 13.
Here, when the aircraft 1 is an unmanned aerial vehicle or the like, it is configured not to have the cockpit 12, and the pilot can wirelessly use a maneuvering unit 123 installed outside or portable. The jet engine 13, the ladder 111, and the rotation suppression ladder 113 may be controlled. Moreover, you may steer by automatic driving. It can also be used as a drone depending on the size and usage.

In addition, the aircraft 1 can be configured to further include the payload mounting portion 2 below the nozzle 14. FIG. 3 is a partial cross-sectional side view showing the payload mounting portion 2 that carries a passenger as an example.
As shown in this figure, the payload mounting portion 2 has a space in which a passenger can be accommodated, and has a window 21 and a seat 22. Moreover, it has the connection part 23 for connecting with the lower surface of the wing | blade 11, for example in the upper part.

  FIG. 4 is a diagram illustrating a state when the payload mounting unit 2 is disposed below the nozzle 14 by the connecting unit 23. As shown in this figure, since the aircraft 1 according to the present disclosure does not blow out air directly below, even if the payload mounting portion 2 is disposed below the nozzle 14, the aircraft 1 floats vertically without affecting the lift. can do. In the present disclosure, the payload mounting unit 2 transports passengers, but may be the payload mounting unit 2 that transports luggage. Here, a separation operation unit 25 that performs an operation of separating the payload mounting unit 2 may be further provided, and the payload mounting unit 2 may include a parachute 24 that operates when the payload mounting unit 2 is separated by the separation operation. Thereby, the payload mounting part 2 can be landed more safely, especially at the time of trouble of the jet engine 13.

As described above, according to the aircraft according to the present embodiment, vertical takeoff and landing can be achieved, and the wind pressure directly below the aircraft can be reduced.
The description of the above-described embodiment is merely an example, and changes and modifications that can be conceived by those skilled in the art are included in the scope of the present invention within the scope of the concept of the present invention. For example, what changed the component of the embodiment into a replaceable configuration and deleted the component are also within the scope of the present invention as long as they are within the scope of the idea of the present invention.

DESCRIPTION OF SYMBOLS 1 Aircraft 11 Wing 111 Ladder 112 Prop 113 Autorotation suppression ladder 12 Cockpit 122 Window 123 Control operation part 13 Jet engine 14 Nozzle 141 Nozzle inlet 142 Nozzle exhaust 143 Current plate 144 Outer nozzle wall 145 Inner nozzle wall 2 Payload mounting Part 21 Window 22 Seat 23 Connecting part 24 Parachute 25 Separation operation part

Claims (9)

A jet engine that jets a jet jet vertically downward;
A nozzle having a nozzle suction port for sucking the jet jet, and a nozzle exhaust port facing in the horizontal direction;
An aircraft comprising: a wing disposed outside the nozzle exhaust port. The nozzle is generally conical,
The nozzle air inlet opens vertically upward near the apex of the conical shape,
The aircraft according to claim 1, wherein the nozzle exhaust port is opened in a ring shape in all outer directions along the circumference of the conical bottom surface.   The aircraft according to claim 1, wherein the nozzle further includes a current plate near the nozzle exhaust port.   The aircraft according to any one of claims 1 to 3, wherein the wing has a ring shape disposed outside the nozzle exhaust port.   The aircraft according to any one of claims 1 to 4, wherein the wing operates to change an angle of a trailing edge and has a plurality of ladders arranged on a circumference.   6. The aircraft according to claim 1, wherein the wing further includes a rotation suppression ladder that extends vertically to the upper surface and changes an angle on the upper surface with reference to an arrangement position of the upper surface.   The aircraft according to any one of claims 1 to 6, further comprising a payload mounting portion below the nozzle. A separation operation unit for performing an operation of separating the payload mounting unit;
The aircraft according to claim 7, wherein the payload mounting portion includes a parachute that operates when the payload mounting portion is separated by a separation operation.   The aircraft according to any one of claims 1 to 8, further comprising a cockpit in which a maneuvering operation unit that performs at least an instruction to control the jet engine is disposed around the jet engine.

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