CN111874226A

CN111874226A - Tilt rotor aircraft

Info

Publication number: CN111874226A
Application number: CN202010656293.4A
Authority: CN
Inventors: 吴志广
Original assignee: Changzhou Huachuang Aviation Technology Co Ltd
Current assignee: Changzhou Huachuang Aviation Technology Co Ltd
Priority date: 2020-07-09
Filing date: 2020-07-09
Publication date: 2020-11-03

Abstract

The invention relates to the technical field of aircrafts, and discloses a tilt rotor aircraft, which comprises: a body; the tail wing is arranged at the tail part of the machine body; at least one pair of side wings, wherein each pair of side wings are symmetrically arranged at two sides of the machine body; the tilting support arms are rotatably connected with the side wings, so that the tilting support arms rotate on a plane parallel to the axial direction of the machine body; at least four rotor wings, every the both ends of the support arm that verts are equipped with one respectively the rotor wing, the rotor wing along with the support arm that verts rotates. The tilt rotor aircraft can take off and land vertically, has the ability that flying speed is fast and load-carrying capacity is strong simultaneously to rotor simple structure can steadily switch between many rotor modes and fixed wing mode.

Description

Tilt rotor aircraft

Technical Field

The invention relates to the technical field of aircrafts, in particular to a tilt rotor aircraft.

Background

The existing aircraft can be divided into a fixed-wing aircraft and a rotor aircraft, wherein the fixed-wing aircraft refers to an aircraft which generates forward thrust or pull force by a power device, generates lift force by fixed wings of a fuselage and flies in the atmosphere. Rotorcraft refers to an aircraft that uses a rotor to provide lift, and can be classified into various types, typically a helicopter and a rotorcraft, according to whether the rotor has a power drive or not. The fixed wing aircraft has the advantages of high speed, large load capacity, high flying height and the like; the rotor craft has the capability of ultra-low altitude flight, low speed (from hovering) and maneuvering flight with unchanged nose direction, can be vertically lifted and landed particularly in small-area fields, and has very wide application.

The fixed-wing aircraft and the rotor aircraft have respective advantages and disadvantages, the fixed-wing aircraft has the biggest limitation that the requirements on a take-off and landing site are high, and the take-off and landing are in great risk, and the rotor aircraft has the biggest limitation that the flying speed is low and the load capacity is poor.

Disclosure of Invention

In order to solve the technical problems, the invention provides a tilt rotor aircraft which can vertically take off and land, has the capabilities of high flying speed and strong load-carrying capacity, has a simple rotor structure, and can be stably switched between a multi-rotor mode and a fixed-wing mode.

The technical scheme provided by the invention is as follows:

a tiltrotor aircraft, comprising:

a body;

the tail wing is arranged at the tail part of the machine body;

at least one pair of side wings, wherein each pair of side wings are symmetrically arranged at two sides of the machine body;

the tilting support arms are rotatably connected with the side wings, so that the tilting support arms rotate on a plane parallel to the axial direction of the machine body;

at least four rotor wings, every the both ends of the support arm that verts are equipped with one respectively the rotor wing, the rotor wing along with the support arm that verts rotates.

In the technical scheme, the tilt rotor aircraft has two modes of a plurality of rotors and a fixed wing, and can vertically take off and land and hover in the air under the mode of the plurality of rotors, so that the tilt rotor aircraft can take off and land without a runway or other devices. After taking off under the multi-rotor mode, can switch between multi-rotor mode and fixed wing mode, can carry out high-speed flight operation under the fixed wing mode, can switch back multi-rotor mode and hover in the air at the point that needs the monitoring of hovering simultaneously. And the landing is switched to a multi-rotor mode for vertical landing. The single aircraft can hover in the air and fly at a high speed and a long distance, the advantages of multiple rotor wings and fixed wings are combined, and the aircraft has a wide application prospect. Simultaneously, rotate through swinging boom and flank and be connected, make the rotor change direction to change the flight state of rotor craft verts, its mounting structure is simpler, makes rotor wing have the practicality, can be used for a plurality of fields such as large aircraft, unmanned vehicles design, flight model aeroplane and model ship.

Further preferably, every two tilting support arms are symmetrically arranged on two sides of the fuselage;

every four rotating wings are symmetrically arranged on two sides of the corresponding side wing in pairs.

Further preferably, every the flank with the support arm junction that verts all is equipped with rotating assembly, and is a plurality of rotating assembly controls respectively correspondingly the support arm that verts round the flank synchronous revolution.

Further preferably, the rotating assembly includes a driving wheel member disposed on the side wing and a driven wheel member disposed on the tilt arm, the driving wheel member being coupled to the driven wheel member to drive the tilt arm to rotate around the side wing.

Further preferably, the driving wheel member includes a speed reducer and a driving gear, the speed reducer is disposed on the side wing, and the driving gear is connected with an output end of the speed reducer;

the driven wheel component comprises a driven gear, the driven gear is arranged on the tilting support arm, and the driven gear is matched and meshed with the driving gear.

Preferably, a baffle is arranged at the end part of the side wing far away from the machine body, the tilting support arm is clamped between the end part of the machine body and the baffle, a pin shaft penetrates through the tilting support arm, and two ends of the pin shaft are respectively fixed on the end part of the machine body and the baffle;

the driven gear is an internal tooth gear with a semicircular structure, and is fixed on the tilting support arm, so that the arc-shaped surface of the driven gear is perpendicular to the pin shaft, and the circle center of the driven gear is positioned on the axis of the pin shaft;

the driving gear is an external tooth gear, is positioned on the inner side of the semicircular structure of the driven gear and is meshed with the driven gear in a matching way.

In the technical scheme, the rotating assembly is realized through an internal gear structure, wherein an external gear serves as a driving wheel, an internal gear ring is fixed with the tilting support arm, the driving torque is amplified through the engagement of the driving wheel and the internal gear ring, and the tilting support arm is driven to rotate; meanwhile, the driven gear is set to be an inner dental wheel with a semicircular structure, the rotating angle of the inner dental wheel is limited, and the tilting support arm rotates around the side wing within the range of 90 degrees.

Further preferably, a driving motor is arranged on the side wing, and the driving motor is connected with the speed reducer and is used for driving the speed reducer to rotate;

the speed reducer is a worm gear speed reducer.

In the technical scheme, the speed reducer is a worm and gear speed reducer, so that a large transmission ratio can be obtained, and the speed reducer is more compact than a staggered shaft helical gear mechanism; the two wheels are in line contact with each other between the meshing tooth surfaces, and the bearing capacity of the mechanism is greatly higher than that of a staggered shaft helical gear mechanism; the worm transmission is equivalent to spiral transmission and is multi-tooth meshing transmission, so that the transmission is stable and the noise is low; when the lead angle of the worm is smaller than the equivalent friction angle between the teeth of the meshing wheel, the mechanism has self-locking performance, and can realize reverse self-locking, namely, only the worm drives the worm wheel, but not the worm is driven by the worm wheel.

Further preferably, the lateral wings are provided with two or more pairs, and the multiple pairs of lateral wings are uniformly arranged along the length direction of the machine body.

In the technical scheme, when the aircraft body is long enough, a plurality of rows of side wings can be arranged on two sides of the aircraft body, each side wing is provided with the tilting support arm and the rotating wing, the structure can be provided with enough rotating wings, so that the rotating wings can provide enough buoyancy or forward thrust, the phase of the rotating wings is changed, the power system of the tilting rotor aircraft is improved, and the aircraft has higher flying speed and load capacity.

Further preferably, every be equipped with two or more on the flank the support arm that verts, it is a plurality of the support arm that verts is followed the length direction of flank evenly sets up.

In this technical scheme, when the flank is enough long-term, can set up a plurality of support arms that vert side by side on the flank, all be provided with the rotor on every support arm that verts, this structure can set up abundant rotor, makes the rotor can provide enough big lift buoyancy or forward thrust, the lifting that becomes the phase of verting rotor craft's driving system, makes it have higher flight speed and load-carrying capacity.

Further preferably, each be equipped with three or three more on the support arm verts rotatory wing, it is a plurality of rotatory wing is followed the length direction of support arm that verts evenly sets up.

In this technical scheme, when the support arm that verts is enough long-term, can set up a plurality of rotor wings side by side on the support arm that verts, this structure can set up abundant rotor wing, makes the rotor wing can provide enough big lift buoyancy or preceding thrust, and the phase-changing promotion vert rotor craft's driving system makes it have higher flight speed and load capacity.

Compared with the prior art, the tilt rotor aircraft has the beneficial effects that:

the tilt rotor aircraft has two modes of multiple rotors and fixed wings, and can vertically take off and land and hover in the air under the multiple rotor mode, so that the tilt rotor aircraft can take off and land without a runway or other devices. After taking off under the multi-rotor mode, can switch between multi-rotor mode and fixed wing mode, can carry out high-speed flight operation under the fixed wing mode, can switch back multi-rotor mode and hover in the air at the point that needs the monitoring of hovering simultaneously. And the landing is switched to a multi-rotor mode for vertical landing. The single aircraft can hover in the air and fly at a high speed and a long distance, the advantages of multiple rotor wings and fixed wings are combined, and the aircraft has a wide application prospect. Simultaneously, rotate through swinging boom and flank and be connected, make the rotor change direction to change the flight state of rotor craft verts, its mounting structure is simpler, makes rotor wing have the practicality, can be used for a plurality of fields such as large aircraft, unmanned vehicles design, flight model aeroplane and model ship.

Drawings

The foregoing features, technical features, advantages and embodiments are further described in the following detailed description of the preferred embodiments, which is to be read in connection with the accompanying drawings.

Fig. 1 is a schematic structural view of a rotor of a tiltrotor aircraft according to the present embodiment in a flight state;

fig. 2 is a schematic structural view of the tilt rotor aircraft of the present embodiment from another perspective of the flight state of the rotor;

fig. 3 is a schematic structural view of the tilt rotor aircraft of the present embodiment from another perspective of the flight state of the rotor;

fig. 4 is a schematic structural diagram of a fixed-wing flight state of the tiltrotor aircraft according to the embodiment;

fig. 5 is a schematic structural view of the tilt rotor aircraft at another view angle in a fixed-wing flight state;

fig. 6 is a schematic structural view of the tilt rotor aircraft at another view angle in a fixed-wing flight state;

fig. 7 is a schematic structural view of a tilt rotor aircraft according to the embodiment in a transitional flight state;

fig. 8 is a schematic structural view of the tilt rotor aircraft of the present embodiment from another perspective of the transitional flight state;

fig. 9 is a schematic structural view of a rotary assembly of the tiltrotor aircraft of the present embodiment;

fig. 10 is a schematic view of a rotary assembly of the tiltrotor aircraft according to another aspect of the present embodiment.

The reference numbers illustrate:

1. the automobile comprises an automobile body, 2 parts of a tail wing, 3 parts of side wings, 4 parts of tilting support arms, 5 parts of rotating wings, 6 parts of rotating assemblies, 7 parts of speed reducers, 8 parts of driving gears, 9 parts of driven gears, 10 parts of baffles, 11 parts of driving motors, 12 parts of rear wheels and 13 parts of front wheels.

Detailed Description

In the following description, for purposes of explanation and not limitation, specific details are set forth, such as particular system structures, techniques, etc. in order to provide a thorough understanding of the embodiments of the present application. However, it will be apparent to one skilled in the art that the present application may be practiced in other embodiments that depart from these specific details. In other instances, detailed descriptions of well-known systems, devices, circuits, and methods are omitted so as not to obscure the description of the present application with unnecessary detail.

It will be understood that the terms "comprises" and/or "comprising," when used in this specification and the appended claims, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof.

For the sake of simplicity, the drawings only schematically show the parts relevant to the present invention, and they do not represent the actual structure as a product. In addition, in order to make the drawings concise and understandable, components having the same structure or function in some of the drawings are only schematically illustrated or only labeled. In this document, "one" means not only "only one" but also a case of "more than one".

It should be further understood that the term "and/or" as used in this specification and the appended claims refers to and includes any and all possible combinations of one or more of the associated listed items.

In the embodiments shown in the drawings, the directions such as up, down, left, right, front, and rear are used to explain the structure and movement of various components of the present invention not absolutely but relatively. These illustrations are appropriate when these components are in the positions shown in the figures. If the description of the positions of these components changes, the indication of these directions changes accordingly.

In addition, in the description of the present application, the terms "first", "second", and the like are used only for distinguishing the description, and are not intended to indicate or imply relative importance.

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following description will be made with reference to the accompanying drawings. It is obvious that the drawings in the following description are only some examples of the invention, and that for a person skilled in the art, other drawings and embodiments can be derived from them without inventive effort.

As a specific embodiment, as shown in fig. 1 to 8, the present embodiment provides a tiltrotor aircraft including: the aircraft comprises an aircraft body 1, a tail wing 2, at least one pair of side wings 3, at least two tilting support arms 4 and at least four rotating wings 5. Wherein, the two empennages 2 are arranged, and the two empennages 2 are symmetrically arranged at the tail part of the machine body 1. A pair of flank 3 symmetry sets up the both sides at fuselage 1, is equipped with an at least support arm 4 that verts on every flank 3, and the support arm 4 that verts rotates with flank 3 to be connected, makes the support arm 4 that verts rotate on the plane parallel with fuselage axial direction. The both ends of every support arm 4 that verts are equipped with a rotor wing 5 respectively, and rotor wing 5 rotates with support arm 4 that verts and is connected to rotate along with support arm 4 that verts. The rotary wing 5 may be a propeller engine as a power output member.

When the tilt rotor aircraft is in a rotor flight state, the tilt support arm 4 and the rotary wing 5 are respectively parallel to the aircraft body 1. At this time, the rotor 5 generates an upward thrust, and the tiltrotor aircraft can hover in the air. By controlling the amount of thrust generated by the rotor wing 5, the tiltrotor aircraft can land stably. When the tilt rotor aircraft is in a fixed wing flight state, the tilt support arm 4 and the rotary wing 5 are respectively perpendicular to the aircraft body 1. At this time, the rotor 5 generates forward thrust, and the tiltrotor aircraft can fly forward at a high speed. By controlling the amount of forward thrust generated by the rotor 5, the flight speed of the tiltrotor aircraft can be controlled. When the tilt rotor aircraft is in a transition flight state, the included angle formed by the tilt support arm 4 and the aircraft body 1 is 0-90 degrees. At this time, the rotary wing 5 generates a forward thrust and an upward thrust. Of course, the turning of the aircraft can also be realized by arranging the rotary wing 5 to rotate relative to the axial direction of the side wing 3.

In this embodiment, the tilt rotor aircraft has two modes of multi-rotor and fixed wing, and can take off and land vertically and hover in the air under the multi-rotor mode, so that the aircraft can take off and land without runways or other devices. After taking off under the multi-rotor mode, can switch between multi-rotor mode and fixed wing mode, can carry out high-speed flight operation under the fixed wing mode, can switch back multi-rotor mode and hover in the air at the point that needs the monitoring of hovering simultaneously. And the landing is switched to a multi-rotor mode for vertical landing. The single aircraft can hover in the air and fly at a high speed and a long distance, the advantages of multiple rotor wings and fixed wings are combined, and the aircraft has a wide application prospect. Simultaneously, rotate through swinging boom and flank and be connected, make the rotor change direction to change the flight state of rotor craft verts, its mounting structure is simpler, makes rotor wing have the practicality, can be used for a plurality of fields such as large aircraft, unmanned vehicles design, flight model aeroplane and model ship.

Specifically, as shown in fig. 1 to 8, two tilting arms 4 are symmetrically disposed on two sides of the fuselage 1, and four rotating wings 5 are symmetrically disposed on two sides of the corresponding side wing 3. Every flank 3 all is equipped with rotating assembly 6 with 4 junctions of the support arm that verts, and a plurality of rotating assembly 6 control respectively that corresponding support arm 4 that verts rotates around flank 3 synchronous revolution. The rotating assembly 6 is used for controlling the tilting arm 4 to rotate around the flank 3 in the directions parallel and perpendicular to the flank, as long as the structure can realize the function.

Further, as shown in fig. 9 and 10, the rotating assembly 6 includes a driving wheel member disposed on the side wing 3 and a driven wheel member disposed on the tilt arm 4, the driving wheel member and the driven wheel member being connected to each other in a fitting manner, and the tilt arm 4 is driven to rotate around the side wing 3. The driving wheel component comprises a speed reducer 7 and a driving gear 8, the speed reducer 7 is arranged on the side wing 3, and the driving gear 8 is connected with the output end of the speed reducer 7. The driven wheel component comprises a driven gear 9, the driven gear 9 is arranged on the tilting support arm 4, and the driven gear 9 is matched and meshed with the driving gear 8.

Specifically, the end of the flank 3, which is far away from the body 1, is provided with a baffle 10, the tilting support arm 4 is clamped between the end of the body 1 and the baffle 10, a pin shaft penetrates through the tilting support arm 4, and two ends of the pin shaft are respectively fixed on the end of the body 1 and the baffle 10, so that the tilting support arm 4 is rotatably connected with the flank 3. The driven gear 9 is an internal gear with a semicircular structure, two ends of the driven gear 9 are respectively fixed on the tilting support arm 4, so that the arc-shaped surface of the driven gear 9 is vertical to the pin shaft, and the circle center of the driven gear 9 is positioned on the axis of the pin shaft. The driving gear 8 is an external tooth gear, and the driving gear 8 is positioned inside the semicircular structure of the driven gear 9 and is in fit engagement with the driven gear 9. The rotating assembly 6 is realized through an internal gear structure, wherein an external gear serves as a driving wheel, an internal gear ring is fixed with the tilting support arm 4, driving torque amplification is realized through the engagement of the driving wheel and the internal gear ring, and the tilting support arm 4 is driven to rotate. Meanwhile, the driven gear 9 is designed as an internal gear with a semicircular structure, the rotation angle of the driven gear is limited, and the tilting arm 4 rotates around the side wing 3 in the directions parallel to and perpendicular to the side wing.

Furthermore, a driving motor 11 is arranged on the side wing 3, and the driving motor 11 is connected with the speed reducer 7 and used for driving the speed reducer 7 to rotate. The driving motor 11 can be arranged outside the side wing 3, the side wing 3 can be arranged to be of a hollow structure, the driving motor 11 is arranged inside the side wing 3, and the driving motor 11 is protected. The speed reducer 7 is preferably a worm gear speed reducer. The worm gear speed reducer can obtain a large transmission ratio, and is more compact than a staggered shaft helical gear mechanism; the two wheels are in line contact with each other between the meshing tooth surfaces, and the bearing capacity of the mechanism is greatly higher than that of a staggered shaft helical gear mechanism; the worm transmission is equivalent to spiral transmission and is multi-tooth meshing transmission, so that the transmission is stable and the noise is low; when the lead angle of the worm is smaller than the equivalent friction angle between the teeth of the meshing wheel, the mechanism has self-locking performance, and can realize reverse self-locking, namely, only the worm drives the worm wheel, but not the worm is driven by the worm wheel.

In another embodiment, as shown in fig. 1 to 3, the present embodiment provides a tiltrotor aircraft based on the above embodiments, including: the aircraft comprises a fuselage 1, a tail wing 2, a side wing 3, a tilting support arm 4 and a rotary wing 5. Wherein, the two empennages 2 are arranged, and the two empennages 2 are symmetrically arranged at the tail part of the machine body 1. The side wings 3 are provided with two or more pairs, and the pairs of side wings 3 are uniformly arranged along the length direction of the machine body 1. Every flank 3 is last to be equipped with one at least and to vert the support arm 4, and the support arm 4 that verts rotates with flank 3 to be connected, and verts the support arm 4 and can rotate around flank 3 in the direction parallel and the vertical direction with the flank. The two ends of each tilting support arm 4 are respectively provided with a rotating wing 5, and the rotating wings 5 and the tilting support arms 4 are relatively fixed and rotate along with the tilting support arms 4. The rotary wing 5 may be a propeller engine as a power output member.

In this embodiment, when the fuselage 1 is long enough, multiple rows of flanks 3 can be arranged on both sides of the fuselage 1, each flank 3 is provided with a tilting support arm 4 and a rotating wing 5, and the structure can be provided with enough rotating wings 5, so that the rotating wings 5 can provide enough buoyancy or forward thrust, and the phase-change lifting of the power system of the tilt rotor aircraft can provide higher flight speed and load capacity.

In another embodiment, as shown in fig. 1 to 3, the present embodiment provides a tiltrotor aircraft based on the above embodiments, including: the aircraft comprises a fuselage 1, a tail wing 2, a side wing 3, a tilting support arm 4 and a rotary wing 5. Wherein, the two empennages 2 are arranged, and the two empennages 2 are symmetrically arranged at the tail part of the machine body 1. A pair of flank 3 symmetry sets up in the both sides of fuselage 1, is equipped with two or more than two support arm 4 that verts on every flank 3, and a plurality of support arm 4 that vert evenly set up along the length direction of flank 3. The tilting arm 4 is rotatably connected to the wing 3, and the tilting arm 4 can rotate around the wing 3 in a direction parallel to and perpendicular to the wing. The two ends of each tilting support arm 4 are respectively provided with a rotating wing 5, and the rotating wings 5 and the tilting support arms 4 are relatively fixed and rotate along with the tilting support arms 4. The rotary wing 5 may be a propeller engine as a power output member.

In this embodiment, when the flank 3 is long enough, can set up a plurality of support arms 4 that vert side by side on the flank 3, all be provided with the rotor wing 5 on every support arm 4 that verts, this structure can set up sufficient rotor wing 5, makes rotor wing 5 can provide enough big lift buoyancy or forward thrust, and the phase-changing has promoted tilt rotor aircraft's driving system, makes it have higher flight speed and load capacity.

In another embodiment, as shown in fig. 1 to 3, the present embodiment provides a tiltrotor aircraft based on the above embodiments, including: the aircraft comprises a fuselage 1, a tail wing 2, a side wing 3, a tilting support arm 4 and a rotary wing 5. Wherein, the two empennages 2 are arranged, and the two empennages 2 are symmetrically arranged at the tail part of the machine body 1. A pair of flank 3 symmetry sets up in the both sides of fuselage 1, is equipped with one at least on every flank 3 and verts the support arm 4, and the support arm 4 that verts rotates with flank 3 to be connected, and verts the support arm 4 and can rotate around flank 3 in parallel and the vertical direction with the flank. Each tilting support arm 4 is provided with three or more than three rotating wings 5, and the plurality of rotating wings 5 are uniformly arranged along the length direction of the tilting support arm 4. The rotary wing 5 is fixed relative to the tilting arm 4 and rotates along with the tilting arm 4. The rotary wing 5 may be a propeller engine as a power output member.

In this embodiment, when the tilting boom 4 is long enough, a plurality of rotary wings 5 can be arranged on the tilting boom 4 side by side, and the structure can be provided with enough rotary wings 5, so that the rotary wings 5 can provide enough buoyancy or forward thrust, and the phase-change lifting of the power system of the tilting rotor aircraft can provide higher flight speed and load capacity.

In the above embodiments, the descriptions of the respective embodiments have respective emphasis, and reference may be made to the related descriptions of other embodiments for parts that are not described or recited in detail in a certain embodiment.

It should be noted that the above embodiments can be freely combined as necessary. The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and decorations can be made without departing from the principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.

Claims

1. A tiltrotor aircraft, comprising:

a body;

the tail wing is arranged at the tail part of the machine body;

2. The tiltrotor aircraft of claim 1, wherein:

each two tilting support arms are symmetrically arranged on two sides of the machine body;

3. The tiltrotor aircraft of claim 2, wherein:

every the flank with it all is equipped with rotating assembly, a plurality of to vert the support arm junction rotating assembly controls respectively and corresponds it rounds to vert the support arm the flank synchronous revolution.

4. The tiltrotor aircraft of claim 3, wherein:

the rotating assembly comprises a driving wheel component and a driven wheel component, the driving wheel component is arranged on the side wing, the driven wheel component is arranged on the tilting support arm, the driving wheel component is connected with the driven wheel component in an adaptive mode, and the driving device drives the tilting support arm to rotate around the side wing.

5. The tiltrotor aircraft of claim 4, wherein:

the driving wheel component comprises a speed reducer and a driving gear, the speed reducer is arranged on the side wing, and the driving gear is connected with the output end of the speed reducer;

6. The tiltrotor aircraft according to claim 5, wherein:

the end part of the side wing, far away from the machine body, is provided with a baffle plate, the tilting support arm is clamped between the end part of the machine body and the baffle plate, a pin shaft penetrates through the tilting support arm, and two ends of the pin shaft are respectively fixed on the end part of the machine body and the baffle plate;

7. The tiltrotor aircraft according to claim 6, wherein:

the driving motor is arranged on the side wing, and is connected with the speed reducer and used for driving the speed reducer to rotate;

the speed reducer is a worm gear speed reducer.

8. The tiltrotor aircraft according to any one of claims 1-7, wherein:

the lateral wings are provided with two or more pairs, and the multiple pairs of lateral wings are uniformly arranged along the length direction of the machine body.

9. The tiltrotor aircraft according to any one of claims 1-7, wherein:

every be equipped with two or more on the flank the support arm that verts, it is a plurality of the support arm that verts is followed the length direction of flank evenly sets up.

10. The tiltrotor aircraft according to any one of claims 1-7, wherein:

every be equipped with three or three more on the support arm verts the rotor, it is a plurality of the rotor is followed the length direction who verts the support arm evenly sets up.