CN218839754U

CN218839754U - Tilting type fixed wing aircraft

Info

Publication number: CN218839754U
Application number: CN202223186301.7U
Authority: CN
Inventors: 孔凌; 植雅芳
Original assignee: Zhaoqing Lingfei Aviation Technology Co ltd
Current assignee: Zhaoqing Lingfei Aviation Technology Co ltd
Priority date: 2022-01-29
Filing date: 2022-11-29
Publication date: 2023-04-11
Anticipated expiration: 2032-11-29

Abstract

The utility model discloses a tilting fixed wing aircraft, which comprises an aircraft body and a rotary swing mechanism; the aircraft body comprises a fuselage and wings arranged on two sides of the fuselage; the rotary swing mechanism is installed on the wing, and comprises a machine arm and a drive, wherein the machine arm and the drive are connected with the wing in a rotating mode, the machine arm winds a servo steering engine for turning the wing, and the rotor wing assembly is installed at the end part of the machine arm and comprises a wing wheel and a drive motor for rotating the wing wheel. Therefore, the utility model discloses an aircraft wing is the horizontality when the state of taking off, has solved the wind-resistance problem, and when horizontal flight, provides power and the control torque that gos forward by the wing wheel, need not pneumatic steering wheel and controls the aircraft, is a simple reliable practical fixed wing aircraft.

Description

Tilting type fixed wing aircraft

Technical Field

The utility model relates to an unmanned aerial vehicle field, in particular to tilting fixed wing aircraft.

Background

The conventional vertical take-off and landing fixed wing aircraft needs a pneumatic steering engine to control the flight attitude in the flight process, a control plane needs a servo steering engine, a linkage rod and other mechanisms, the complexity of the aircraft is increased, and the four-rotor tailstock type aircraft can realize flight without control plane control, but the wings are in a vertical state during vertical take-off, so that the wind area is large, and the wind resistance is extremely poor.

SUMMERY OF THE UTILITY MODEL

The utility model discloses aim at solving one of the technical problem that exists among the prior art at least. Therefore, the utility model provides a tilting fixed wing aircraft has solved the wind resistance problem when taking off the state, and when horizontal flight, need not pneumatic steering wheel and control the flight, and simple structure is reliable.

The utility model provides a technical scheme that its technical problem adopted is:

a tilting fixed-wing aircraft comprises an aircraft body and a rotating and swinging mechanism; the aircraft body comprises a fuselage and wings arranged on two sides of the fuselage; the rotary swing mechanism is installed on the wing and comprises a machine arm, a drive mechanism and a rotor wing assembly, wherein the machine arm is connected with the wing in a rotating mode, the drive mechanism drives the machine arm to wind a servo steering engine for turning over the wing, the rotor wing assembly is installed at the end portion of the machine arm, and the rotor wing assembly comprises a wing wheel and a drive motor for rotating the wing wheel.

According to the utility model discloses tilting fixed wing aircraft has following beneficial effect at least: when taking off, the aircraft arms and the wings are in a horizontal state, the rotor wing assemblies of the aircraft are driven by the motor to rotate to generate thrust to lift off the ground in the state, the flight attitude control principle is consistent with that of a common multi-rotor aircraft, and the wings do not generate lift force, so that the problem of wind resistance in the taking off state is solved. When the horizontal flight switching height is reached, the servo steering engines of the wings on the two sides drive the arms on the two sides to simultaneously turn around the wings for a certain angle, the wings keep a favorable attack angle state in the turning process, the current advancing speed is gradually improved, the lifting force generated by the wings is also gradually improved, when the lifting force generated by the wings can counteract the gravity of the aircraft, the angles of the arms on the two sides are turned to 90 degrees to enter a fixed wing flight state, the wing wheels become forward pulling power in the state, the lifting force required by the aircraft is provided by the wings, the wing wheels provide forward power and control torque, and the flight attitude realizes acceleration and deceleration, climbing, diving, turning and rolling by the differential motion of the wing wheels, so that a pneumatic steering engine is not required to control the aircraft. It needs to supplement that servo steering engine drive horn rotation turned angle is set for by flight control system, receives the relevant order of flying to control and just rotates, so when the horn rotated the angle that requires, reached promptly and fly to control the value set, fly to control no longer output command signal, servo steering engine axis of rotation locks, consequently the horn position is locked fixedly, guarantees to fly steadily.

According to some embodiments of the utility model, the top surface of wing includes last cambered surface and lower cambered surface, the junction of going up cambered surface and lower cambered surface is equipped with the lift line, the horn with the hookup location of wing is located near the lift line.

The beneficial results are: therefore, the installation of the horn is facilitated, the influence on the wing is reduced, and the balance of the wing in flying is guaranteed.

According to some embodiments of the invention, the swinging mechanism is arranged at an end of the wing.

The beneficial results are: the installation is easy like this, need not make great change to the structure of wing, can not touch the fuselage when adopting great rotor to rotate.

According to some embodiments of the invention, the wing is provided with two the swing mechanism, one the swing mechanism is located on the wing, another the swing mechanism is located the tip of wing.

The beneficial results are: therefore, the swing mechanism can provide larger lift force in a horizontal state and provide larger advancing power in a vertical state, and meanwhile, the wing cannot occupy too much space. Therefore, each rotary swing mechanism can keep a certain working distance, and the wing is uniformly stressed.

According to some embodiments of the invention, the tip of wing is equipped with the concave position, concave position installation the horn.

The beneficial results are: the concave position is arranged to conveniently accommodate and mount the horn at the end part of the wing, so that the horn is prevented from protruding out of the end part of the wing, and the effect of protecting the horn mounting position is achieved.

According to some embodiments of the utility model, the horn includes upper arm, underarm, connection the upper arm with the pivot of underarm, the pivot pass through the gear with servo steering wheel connects, the tip of upper arm with a rotor is respectively installed to the tip of underarm.

The beneficial results are: the upper arm sets up the upside at the wing like this, and the underarm setting is at the downside of wing, and at pivot pivoted in-process, upper arm and underarm keep balance like this, and four rotors accomplish the process of taking off and control flight jointly simultaneously, and the pivot passes through the gear to be connected with servo steering wheel and can play the effect of speed reduction, makes the horn upset steady.

According to some embodiments of the utility model, be equipped with the installing port that the holding horn runs through on the wing, the installing port installation the pivot, the side of installing port wing internally mounted servo steering wheel with the gear.

The beneficial results are: set up installing port holding horn, the horn of being convenient for runs through and installs on the wing, does not influence the pivot simultaneously and drives the upset of upper arm and underarm, and servo steering wheel and gear are installed inside the wing, and compact structure reduces air resistance.

According to some embodiments of the invention, the upper arm with the lower arm staggers the setting.

The beneficial results are: the arrangement is favorable for the rotating shaft to drive the upper arm and the lower arm to overturn, and meanwhile, the installation opening is not required to be too large, so that the wing keeps certain strength.

According to some embodiments of the utility model, the wing includes main wing and wingtip, the main wing with the fuselage is connected, the horn install in the main wing, the servo steering wheel is installed the main wing, the horn with the servo steering wheel is connected, the wingtip with horn fixed mounting.

The beneficial results are: therefore, the wing tip can be driven to turn when the horn turns, and adjustment with more functions is realized.

According to some embodiments of the invention, the wing tip is arranged offset from the horn.

The beneficial results are: during takeoff, the arm is in a horizontal state, the wingtips are in a vertical state, ascending resistance can be reduced, in the tilting switching process, the arm and the wingtips tilt synchronously, after the tilting switching is completed, the arm is in a vertical state, the wingtips rotate to the horizontal state and form a pneumatic whole with the main wing, and the lifting force is increased.

Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.

Drawings

The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:

fig. 1 is a schematic view of a first embodiment of the present invention;

FIG. 2 is an internal schematic view at A of FIG. 1;

FIG. 3 is a schematic view of another embodiment of FIG. 1;

FIG. 4 is a schematic view of a second embodiment of the present invention;

fig. 5 is a schematic view of a third embodiment of the present invention;

fig. 6 is a schematic view of a fourth embodiment of the present invention;

figure 7 is a schematic view of the installation of the wing tip and horn of figure 6.

Reference numerals: the aircraft comprises a fuselage 100, wings 110, an arm 120, a servo steering engine 130, a rotor assembly 140, a wing wheel 150, a motor 160, a lifting line 170, a recess 180, an upper arm 190, a lower arm 200, a rotating shaft 210, a gear 220, a mounting opening 230, a main wing 240 and a wing tip 250.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are exemplary only for explaining the present invention, and should not be construed as limiting the present invention.

In the description of the present invention, it should be understood that the directional descriptions, such as the directions or positional relationships indicated by upper, lower, front, rear, left, right, etc., are based on the directions or positional relationships shown in the drawings, and are only for convenience of description and simplification of the description, but not for indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and thus should not be construed as limiting the present invention.

In the description of the present invention, a plurality of means are one or more, a plurality of means are two or more, and the terms greater than, less than, exceeding, etc. are understood as not including the number, and the terms greater than, less than, within, etc. are understood as including the number. If the first and second are described for the purpose of distinguishing technical features, they are not to be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.

In the description of the present invention, unless there is an explicit limitation, the words such as setting, installation, connection, etc. should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above words in combination with the specific contents of the technical solution.

A tilting fixed wing aircraft is described in detail in four specific embodiments with reference to fig. 1-7. It is to be understood that the following description is illustrative only and is not intended as a specific limitation on the invention.

As shown in fig. 1 to 3, in a first embodiment of the present invention, a tilt-type fixed-wing aircraft includes an aircraft body and a swing mechanism.

The aircraft body comprises a fuselage 100 and wings 110 arranged on two sides of the fuselage 100; the rotary swing mechanism is installed on the wing 110, and comprises a horn 120 connected with the wing 110 in a rotating manner, a servo steering engine 130 driving the horn 120 to turn around the wing 110, and a rotor assembly 140 installed at the end part of the horn 120, wherein the rotor assembly 140 comprises a wing wheel 150 and a motor 160 driving the wing wheel 150 to rotate. During takeoff, as shown in fig. 1, the horn 120 and the wing 110 are both in a horizontal state, in this state, the rotor assembly 140 of the aircraft is driven by the motor 160 to rotate the wing wheel 150 to generate thrust to lift off the ground, the flight attitude control principle is consistent with that of a common multi-rotor aircraft, and the wing 110 does not generate lift force, so that the wind resistance problem during takeoff is solved. After the level flight switching height is reached, as shown in fig. 3, the servo steering engines 130 of the wings 110 on both sides drive the arms 120 on both sides to simultaneously turn over around the wings 110 by a certain angle, the wings 110 maintain a favorable attack angle state in the turning process, the current advancing speed is gradually increased, the lift force generated by the wings 110 is also gradually increased, when the lift force generated by the wings 110 can counteract the gravity of the aircraft, the angles of the arms 120 on both sides are turned to 90 degrees to enter a fixed-wing flight state, the wing wheels 150 become forward pulling power in the state, the lift force required by the aircraft is provided by the wings 110, the wing wheels 150 provide forward power and control torque, and the flight attitude realizes acceleration and deceleration, climbing, diving, turning and rolling by the differential motion of the wing wheels 150, so that the aircraft does not need to be controlled by pneumatic steering engines. It should be added that the servo steering engine 130 drives the horn 120 to rotate by a rotation angle set by the flight control system, and the horn 120 rotates only when receiving a relevant command of flight control, so that when the horn 120 rotates to a required angle, the set value of flight control is reached, the flight control does not output a command signal any more, the rotation shaft of the servo steering engine 130 is locked, and therefore the position of the horn 120 is locked and fixed, and stable flight is ensured.

Specifically, the top surface of the wing 110 includes an upper arc surface and a lower arc surface, a lift line 170 is provided at a connection position of the upper arc surface and the lower arc surface, and a connection position of the horn 120 and the wing 110 is located near the lift line 170. This facilitates the mounting of the horn 120 while reducing the impact on the wing 110 and ensuring that the wing 110 remains balanced during flight.

As shown in fig. 4, the swinging mechanism is provided at the end of the wing 110. This arrangement is easy to install, does not require major structural modifications to the wing 110, and does not encounter the fuselage 100 when a larger rotor is used for rotation.

As shown in fig. 5, one wing 110 is provided with two swinging mechanisms, one swinging mechanism is located on the wing 110, and the other swinging mechanism is located at the end of the wing 110. This provides more lift when the slewing mechanism is in the horizontal position and more forward power when the slewing mechanism is in the vertical position, without taking up too much space on the wing 110. This is beneficial to keep a certain working distance of each swing mechanism and also to make the wing 110 uniformly stressed.

Specifically, the end of the wing 110 is provided with a recess 180, and the recess 180 mounts the horn 120. The concave part 180 is arranged to accommodate the horn 120 at the end of the wing 110, and to prevent the horn 120 from protruding out of the end of the wing 110, so as to protect the installation position of the horn 120.

As shown in fig. 2, the horn 120 includes an upper arm 190, a lower arm 200, and a shaft 210 connecting the upper arm 190 and the lower arm 200, the shaft 210 is connected to the servo steering gear 130 through a gear 220, and a rotor is mounted on each of the end portions of the upper arm 190 and the lower arm 200. Like this upper arm 190 sets up the upside at wing 110, and lower arm 200 sets up the downside at wing 110, and at the pivoted in-process of pivot 210 like this, upper arm 190 and lower arm 200 keep balance, and four rotors accomplish the process of taking off and control flight jointly simultaneously, and pivot 210 is connected through gear 220 and servo steering engine 130 and can be played the effect of slowing down, makes horn 120 upset steady.

As shown in fig. 1 and 2, the wing 110 is provided with an installation opening 230 for accommodating the horn 120, the installation opening 230 is provided with the rotating shaft 210, and the servo steering engine 130 and the gear 220 are installed inside the wing 110 on the side of the installation opening 230. The mounting port 230 is arranged to accommodate the horn 120, so that the horn 120 can be conveniently installed on the wing 110 in a penetrating manner, the rotating shaft 210 is not influenced to drive the upper arm 190 and the lower arm 200 to overturn, the servo steering engine 130 and the gear 220 are installed inside the wing 110, the structure is compact, and air resistance is reduced.

Further, the upper arm 190 and the lower arm 200 are disposed in a staggered manner. This arrangement facilitates the rotation of the shaft 210 to turn the upper arm 190 and the lower arm 200, and the mounting opening 230 is not too large, so that the wing 110 can maintain a certain strength.

As shown in fig. 6, the wing 110 includes a main wing 240 and a wing tip 250, the main wing 240 is connected to the fuselage 100, the horn 120 is mounted to the main wing 240, the servo steering engine 130 is mounted to the main wing 240, and the horn 120 is connected to the servo steering engine 130, as shown in fig. 7, the wing tip 250 and the horn 120 are fixedly mounted by screws, so that the horn 120 can drive the wing tip 250 to turn over when turning over, thereby achieving adjustment of more functions.

Note that the wing tip 250 is offset from the horn 120. As shown in fig. 7, during takeoff, the arm 120 is in a horizontal state, the wing tip 250 is in a vertical state, so that the ascending resistance can be reduced, during the tilting switching process, the arm 120 and the wing tip 250 tilt synchronously, after the tilting switching process is completed, the arm 120 is in a vertical state, the wing tip 250 rotates to a horizontal state, and the main wing 240 becomes an aerodynamic whole, so that the ascending force is increased.

The embodiments of the present invention have been described in detail with reference to the drawings, but the present invention is not limited to the above embodiments, and various changes can be made without departing from the spirit of the present invention within the knowledge of those skilled in the art.

Claims

1. A tilting fixed wing aircraft, comprising:

the aircraft comprises an aircraft body and a control system, wherein the aircraft body comprises a fuselage (100) and wings (110) arranged on two sides of the fuselage (100);

the rotary swing mechanism is installed on the wing (110), and comprises a horn (120) rotationally connected with the wing (110), a servo steering engine (130) for driving the horn (120) to rotate around the wing (110), and a rotor wing assembly (140) installed at the end part of the horn (120), wherein the rotor wing assembly (140) comprises a wing wheel (150) and a motor (160) for driving the wing wheel (150) to rotate.

2. The tilting fixed wing aircraft of claim 1, wherein the top surface of the wing (110) comprises an upper cambered surface and a lower cambered surface, the connection of the upper cambered surface and the lower cambered surface is provided with a lift line (170), and the connection position of the horn (120) and the wing (110) is located near the lift line (170).

3. A tilting fixed wing aircraft according to claim 1, wherein said swivel mechanism is provided at the end of said wing (110).

4. A tilting fixed wing aircraft according to claim 1, wherein one said wing (110) is provided with two said swivel mechanisms, one said swivel mechanism being located on said wing (110) and the other said swivel mechanism being located at the end of said wing (110).

5. A tilting fixed wing aircraft according to claim 3 or 4, characterized in that the end of the wing (110) is provided with a recess (180), said recess (180) mounting the horn (120).

6. The tilting fixed wing aircraft according to claim 1, wherein the horn (120) comprises an upper arm (190), a lower arm (200), and a rotating shaft (210) connecting the upper arm (190) and the lower arm (200), the rotating shaft (210) is connected with the servo steering engine (130) through a gear (220), and one rotor assembly (140) is mounted at each of the end of the upper arm (190) and the end of the lower arm (200).

7. The tilting fixed-wing aircraft according to claim 6, wherein the wing (110) is provided with a mounting opening (230) for receiving the horn (120) to penetrate through, the rotating shaft (210) is mounted on the mounting opening (230), and the servo steering engine (130) and the gear (220) are mounted inside the wing (110) on the side of the mounting opening (230).

8. The tilting fixed wing aircraft of claim 6, wherein said upper arm (190) and said lower arm (200) are offset.

9. The tilting fixed wing aircraft according to claim 1, wherein the wing (110) comprises a main wing (240) and a wing tip (250), the main wing (240) is connected with the fuselage (100), the servo steering engine (130) is installed on the main wing (240), the horn (120) is connected with the servo steering engine (130), and the wing tip (250) is fixedly installed on the horn (120).

10. The tilting fixed wing aircraft of claim 9, wherein said wingtip (250) is offset from said horn (120).