CN217456346U - Multi-state aircraft - Google Patents

Abstract

The utility model discloses a polymorphic aircraft, include: the method comprises the following steps: the device comprises a machine body, a connecting rod and a connecting rod, wherein the machine body comprises an upper connecting rod and a lower connecting rod which are limited to be of a parallelogram structure; the wing comprises a front wing and a rear wing, the front wing and the rear wing are positioned at two ends of the fuselage, two ends of the upper connecting rod are respectively hinged with the upper part of the front wing and the upper part of the rear wing, two ends of the lower connecting rod are hinged with the lower part of the front wing and the lower part of the rear wing, the front wing and the rear wing are rotatably provided with rotors, and the rotors face to one side of the upper connecting rod, which is far away from the lower connecting rod; the telescopic mechanism is hinged to the airplane body, and a telescopic end of the telescopic mechanism is connected with the wings. The two ends of the upper connecting rod are hinged to the upper portions of the front wings and the upper portions of the rear wings, and the two ends of the lower connecting rod are hinged to the lower portions of the front wings and the lower portions of the rear wings, so that the aircraft body and the wings are in linkage change, the free switching between vertical lifting and horizontal flying is achieved, the operation is simple and convenient, and the stability and the safety of the aircraft are improved.

Description

Multi-state aircraft

Technical Field

The utility model relates to a middle-size and small-size aircraft technical field, in particular to polymorphic aircraft.

Background

Conventional multi-rotor aircraft rely on the forces generated by the multiple rotors to overcome gravity and provide the power to advance. In the horizontal forward flight process, only a part of force generated by the rotors is used for providing forward power, and the rest force is used for providing upward lift force to overcome gravity to keep the height, so that the power consumption is high, the efficiency is low, and the cruising ability is insufficient.

For example, the invention is a chinese patent CN103072688A, the name of the invention is "tiltable four-rotor aircraft", and a rotor steering device carrying rotors is installed on four fixed wings, and when the rotor steering device tilts, the rotor is driven to rotate, so that the conversion between the horizontal forward flight mode and the vertical lift flight mode of the aircraft is realized, that is, the fuselage is maintained not to tilt, the power device is rotated, and the direction of the force generated by the power device tilts between the approximately vertical direction and the approximately horizontal direction, which is embodied in the penc type fighter in the uk and the F35B fighter in the usa. These designs generally require complex mechanical structures and more parts, and the maintenance requirements for these mechanical structures and parts are also higher, which inevitably reduces the reliability and increases the maintenance difficulty and cost.

For another example, the invention is a chinese patent CN105000179A, the name of which is "tilt fuselage type hybrid multi-state aircraft", and three flight states of vertical take-off and landing or fixed-point hovering state, cruise flight state, and transition state of the aircraft are realized by adjusting the rotation speeds of four rotors. In all the components, the relative positions of other components are unchanged except that the rotating shafts of the propeller and the motor can normally rotate. Particularly, the installation positions of the fuselage, the motor and the propeller are relatively fixed, so that the stability in flight is poor and the operation is difficult.

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 polymorphic aircraft, can realize vertical lift and the free switching of horizontal flight, easy and simple to handle, improve the stability and the security of aircraft.

According to the utility model discloses polymorphic aircraft, include: the device comprises a machine body, a connecting rod and a connecting rod, wherein the machine body comprises an upper connecting rod and a lower connecting rod which are limited to be of a parallelogram structure; the wing comprises a front wing and a rear wing, the front wing and the rear wing are positioned at two ends of the fuselage, two ends of the upper connecting rod are respectively hinged with the upper part of the front wing and the upper part of the rear wing, two ends of the lower connecting rod are hinged with the lower part of the front wing and the lower part of the rear wing, the front wing and the rear wing are rotatably provided with rotors, and the rotors face to one side of the upper connecting rod, which is far away from the lower connecting rod; the telescopic mechanism is hinged to the airplane body, the telescopic end of the telescopic mechanism is connected with the wings, and the telescopic mechanism moves to enable the wings to incline or reset.

According to the utility model discloses polymorphic aircraft, following beneficial effect has at least: the rotor wing rotates to enable the front wing and the rear wing to generate lift force, so that the aircraft ascends; when the aircraft needs horizontal flight, the telescopic mechanism moves to enable the wings to incline towards one side, and at the moment, the aircraft is changed into a parallelogram structure, so that the aircraft is converted from vertical rising to horizontal flight; when the aircraft needs to land, the telescopic mechanism moves to enable the wings to reset towards one side, so that the aircraft is converted from horizontal flight to vertical landing. The two ends of the upper connecting rod are hinged to the upper portions of the front wings and the upper portions of the rear wings, and the two ends of the lower connecting rod are hinged to the lower portions of the front wings and the lower portions of the rear wings, so that the aircraft body and the wings are in linkage change, the free switching between vertical lifting and horizontal flying is achieved, the operation is simple and convenient, and the stability and the safety of the aircraft are improved.

According to the utility model discloses polymorphic aircraft, telescopic machanism include the cylinder, the cylinder articulate in the fuselage, the piston of cylinder with the front wing is connected.

According to the utility model discloses polymorphic aircraft, telescopic machanism include driving motor, driving motor is provided with the screw rod, the front wing is provided with the nut, the screw rod with nut looks adaptation.

According to the embodiment of the utility model provides a polymorphic aircraft, still include angle detecting element and controller, angle detecting element set up in the fuselage, angle detecting element is used for the output the fuselage with the angle information of wing, the controller with angle detecting element telescopic machanism connects.

According to the utility model discloses polymorphic aircraft, the rotor include rotor motor and screw, the front wing with the back wing is provided with rotor motor, the screw with rotor motor's output shaft, rotor motor with the controller is connected.

According to the embodiment of the utility model provides a polymorphic aircraft, go up the connecting rod with the connecting rod is provided with two respectively down, two go up and be provided with the guide bar between the connecting rod, two the fixed dead lever that is provided with down between the connecting rod, telescopic machanism respectively with the guide bar the dead lever is articulated.

According to the embodiment of the utility model provides a polymorphic aircraft, the front wing rotates and is provided with the front rudder plate, the back wing rotates and is provided with the back rudder plate, the front rudder plate is located the both ends of front wing, the back rudder plate is located the both ends of back wing.

According to the utility model discloses polymorphic aircraft, the front wing rotate and to be provided with preceding dihedral, the rear wing rotates and is provided with back dihedral, preceding rudder plate rotate set up in preceding dihedral, back rudder plate rotate set up in back dihedral.

According to the utility model discloses polymorphic aircraft, preceding dihedral with back dihedral all is provided with the opening, the opening with preceding rudder plate back rudder plate looks adaptation.

According to the embodiment of the utility model provides a polymorphic aircraft, the front wing with the back wing is provided with the gyro wheel.

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 structural view of a multi-state aircraft according to an embodiment of the present invention;

fig. 2 is a schematic structural view of a multi-state aircraft according to some embodiments of the present invention;

fig. 3 is a schematic structural view of a multi-state aircraft according to some embodiments of the present invention;

FIG. 4 is an enlarged view at A in FIG. 3;

FIG. 5 is a front elevation view of a multi-modal aircraft in a vertical ascent and descent in accordance with an embodiment of the present invention;

FIG. 6 is a front view of a multi-state aircraft in a switched flight state in accordance with an embodiment of the present invention;

fig. 7 is a front view of the multi-modal aircraft of an embodiment of the present invention in horizontal flight.

Description of reference numerals:

an upper link 110; a lower link 120; a front wing 210; a rear wing 220; a rotor 230; rotor motor 231; a propeller 232; a front rudder plate 240; a rear rudder plate 250; a leading dihedral angle 260; a back dihedral 270; a roller 280; a telescoping mechanism 310; a cylinder 320; a drive motor 330; a screw 340; a nut 350.

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 drawings are exemplary only for the purpose of 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 orientation or positional relationship indicated with respect to the orientation description, such as up, down, front, rear, left, right, etc., is based on the orientation or positional relationship shown in the drawings, and is only for convenience of description and simplification of description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, 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.

Referring to fig. 1-7, an embodiment of the present invention provides a multi-state aircraft, including a fuselage, wings, and a telescoping mechanism 310. The fuselage comprises an upper connecting rod 110 and a lower connecting rod 120, and the upper connecting rod 110 and the lower connecting rod 120 are limited to be of a parallelogram structure; the wings comprise a front wing 210 and a rear wing 220, the front wing 210 and the rear wing 220 are positioned at two ends of the fuselage, two ends of the upper connecting rod 110 are respectively hinged with the upper part of the front wing 210 and the upper part of the rear wing 220, two ends of the lower connecting rod 120 are hinged with the lower part of the front wing 210 and the lower part of the rear wing 220, the front wing 210 and the rear wing 220 are rotatably provided with a rotor wing 230, and the rotor wing 230 faces to one side of the upper connecting rod 110 away from the lower connecting rod 120; the telescopic mechanism 310 is hinged to the fuselage, the telescopic end of the telescopic mechanism 310 is connected with the wing, and the telescopic mechanism 310 moves to enable the wing to incline or reset.

The rotor 230 rotates to make the front wing 210 and the rear wing 220 generate lift force, thereby realizing the vertical ascent of the aircraft; when the aircraft needs horizontal flight, the telescopic mechanism 310 moves to enable the wings to incline towards one side, and at the moment, the aircraft is changed into a parallelogram structure, so that the aircraft is converted from vertical rising to horizontal flight; when the aircraft needs to land, the telescopic mechanism 310 moves to reset the wings, so that the aircraft is converted from horizontal flight to vertical landing. The two ends of the upper connecting rod 110 are hinged to the upper parts of the front wings 210 and the upper parts of the rear wings 220, and the two ends of the lower connecting rod 120 are hinged to the lower parts of the front wings 210 and the lower parts of the rear wings 220, so that the aircraft body and the wings are in linkage change, the free switching between vertical lifting and horizontal flying is realized, the operation is simple and convenient, and the stability and the safety of the aircraft are improved.

Referring to fig. 1 to 7, the telescopic mechanism 310 is hinged to the fuselage, the telescopic end of the telescopic mechanism 310 is connected to the wing, and the telescopic mechanism 310 moves to incline or reposition the wing. Specifically, a guide rod is arranged between the two upper connecting rods 110, a fixed rod is arranged between the two lower connecting rods 120, the telescopic mechanism 310 is hinged to the guide rod and the fixed rod, and the telescopic end of the telescopic mechanism 310 is connected to the wing. Through being provided with guide bar and dead lever, be convenient for install telescopic machanism 310, and improve the stability that aircraft flight state freely switched.

Referring to fig. 2, in some embodiments, the telescoping mechanism 310 includes a cylinder 320, the cylinder 320 is hinged to the lower link 120, and a piston of the cylinder 320 is connected to the front wing 210. The piston of the cylinder 320 moves to tilt or reset the front wing 210, and further drives the rear wing 220 to tilt or reset, so as to realize free switching between vertical lifting and horizontal flying, and the operation is simple and convenient. It is contemplated that the piston of the cylinder 320 may be configured to be coupled to the rear wing 220, and the present invention is not limited thereto.

Referring to fig. 3 and 4, in another embodiment, the telescoping mechanism 310 includes a driving motor 330, the driving motor 330 is provided with a screw 340, the front wing 210 is provided with a nut 350, and the nut 350 is matched with the screw 340. The driving motor 330 drives the screw 340 to rotate, so that the nut 350 slides to drive the front wing 210 to incline or reset, thereby realizing free switching of vertical lifting and horizontal flying, and having simple structure and convenient operation.

Referring to fig. 1 to 7, the front wing 210 and the rear wing 220 are provided in a strip plate-shaped structure. The front wing 210 is disposed at the right end of the upper link 110 and the lower link 120, the rear wing 220 corresponds to the front wing 210, and the rear wing 220 is disposed at the left end of the upper link 110 and the lower link 120. The upper connecting rod 110 and the lower connecting rod 120 are respectively provided with two, two ends of the upper connecting rod 110 are respectively hinged with the upper part of the front wing 210 and the upper part of the rear wing 220, two ends of the lower connecting rod 120 are respectively hinged with the lower part of the front wing 210 and the lower part of the rear wing 220, and the front wing 210, the rear wing 220, the upper connecting rod 110 and the lower connecting rod 120 are limited to form a deformable prism frame structure. Specifically, the front wing 210 and the rear wing 220 are both provided with a connecting shaft, both ends of the upper connecting rod 110 and the lower connecting rod 120 are both provided with a connecting hole adapted to the connecting shaft, and the connecting shaft is matched with the connecting hole, so that both ends of the upper connecting rod 110 are hinged to the front wing 210 and the rear wing 220, and both ends of the lower connecting rod 120 are correspondingly hinged to the front wing 210 and the rear wing 220. Conceivably, both the front wing 210 and the rear wing 220 are provided with openings, and the connecting shaft is located in the openings, so that additional parts are not needed to fix the connecting shaft, the installation is convenient, and the weight of the aircraft can be reduced. It should be noted that connecting holes may also be provided on the front wing 210 and the rear wing 220, and the upper connecting rod 110 and the lower connecting rod 120 are provided with connecting shafts; alternatively, the front wing 210 and the rear wing 220, and the upper link 110 and the lower link 120 are provided with connection holes, and are coupled with the nut 350 through bolts to realize the hinge.

Referring to fig. 1 to 7, the rotor 230 includes a rotor 230 motor and a propeller 232, the rotor 230 motor is vertically disposed on the upper portions of the front wing 210 and the rear wing 220, and the propeller 232 is connected to an output shaft of the rotor 230 motor. Rotor 230 is rotated by a motor, which rotates propeller 232, thereby flying the aircraft. Wherein, screw 232 is provided with the pivot, and the output shaft and the pivot of rotor 230 motor pass through shaft coupling fixed connection. Rotor 230 motor drive pivot is rotated to drive screw 232 and rotate, simple structure, it is easy and simple to handle. It should be noted that the rotor 230 may also be hinged to the front wing 210 and the rear wing 220, and at this time, the propeller 232 may also rotate relative to the front wing 210 and the rear wing 220, so as to be suitable for different flight environments.

Referring to fig. 1 to 7, in some embodiments, the front wing 210 is rotatably provided with a front rudder plate 240, the rear wing 220 is rotatably provided with a rear rudder plate 250, the front rudder plate 240 is located at both ends of the front wing 210, and the rear rudder plate 250 is located at both ends of the rear wing 220. By adjusting the angle between the front rudder plate 240 and the front wing 210 and the angle between the rear rudder plate 250 and the rear wing 220, the motions such as pitch, roll, and horizontal yaw of the aircraft can be realized. It is conceivable that the front wing 210 is rotatably provided with a dihedral angle 260, the front rudder plate 240 is rotatably provided with a dihedral angle 260, the rear wing 220 is rotatably provided with a dihedral angle 270, and the rear rudder plate 250 is rotatably provided with a dihedral angle 270. By arranging the front dihedral angle 260 and the rear dihedral angle 270, the stability of the aircraft in roll and horizontal rotation can be improved, and the safety performance is improved. It is easy to understand that, the dihedral angle 260 and the dihedral angle 270 are both provided with openings, and the openings are matched with the front rudder plate 240 and the rear rudder plate 250, so that the overall weight of the aircraft can be reduced, and the flight stability can be improved. The front wing 210 and the rear wing 220 are provided with rollers 280 on the sides far away from the rotor 230, so that the aircraft can slide on the ground, and the application range is expanded to meet different flight environments.

The multi-state aircraft further comprises an angle detection element and a controller, the angle detection element is arranged on the fuselage and used for outputting angle information of the fuselage and the wings, and the controller is connected with the angle detection element and the telescopic mechanism 310. The angle detection element outputs the angle information of the fuselage and the wings and feeds the information back to the controller, and the controller controls the telescopic mechanism 310 to move and work so as to realize the inclination or reset of the wings, so that the operation is simple and convenient. It is conceivable that the controller is connected with the rotor 230 motor, the front rudder plate 240, the rear rudder plate 250, the dihedral angle 260 and the dihedral angle 270, and the controller controls the rotor 230 motor, the front rudder plate 240, the rear rudder plate 250, the dihedral angle 260 and the dihedral angle 270 to move for operation.

In the description herein, references to the description of the term "one embodiment," "some embodiments," "an illustrative embodiment," "an example," "a specific example," or "some examples" or the like mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

While embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.

Claims (10)

1. Polymorphic aircraft, characterized in that includes:

the device comprises a machine body, a connecting rod and a connecting rod, wherein the machine body comprises an upper connecting rod and a lower connecting rod which are limited to be of a parallelogram structure;

the wing comprises a front wing and a rear wing, the front wing and the rear wing are positioned at two ends of the fuselage, two ends of the upper connecting rod are respectively hinged with the upper part of the front wing and the upper part of the rear wing, two ends of the lower connecting rod are hinged with the lower part of the front wing and the lower part of the rear wing, the front wing and the rear wing are rotatably provided with rotors, and the rotors face to one side of the upper connecting rod, which is far away from the lower connecting rod;

the telescopic mechanism is hinged to the airplane body, the telescopic end of the telescopic mechanism is connected with the wings, and the telescopic mechanism moves to enable the wings to incline or reset.

2. The multi-state aircraft of claim 1, wherein the telescoping mechanism comprises a cylinder hinged to the fuselage, a piston of the cylinder being connected to the front wing.

3. The multi-modal aircraft of claim 1, wherein the telescoping mechanism comprises a drive motor provided with a threaded rod and the front wing is provided with a nut, the threaded rod fitting with the nut.

4. The multi-state aircraft of claim 2 or 3, further comprising an angle detection element disposed on the fuselage for outputting angle information of the fuselage and the wing, and a controller connected to the angle detection element and the telescoping mechanism.

5. The multi-state aircraft of claim 4, wherein the rotor includes a rotor motor and a propeller, the front wing and the rear wing having the rotor motor disposed thereon, the propeller being coupled to an output shaft of the rotor motor, the rotor motor being coupled to the controller.

6. The multi-state aircraft of claim 1, wherein there are two upper links and two lower links, a guide rod is disposed between the two upper links, a fixed rod is fixedly disposed between the two lower links, and two ends of the telescoping mechanism are connected to the guide rod and the fixed rod, respectively.

7. The multi-state aircraft of claim 1, wherein the front wing is rotatably provided with a front rudder plate, the rear wing is rotatably provided with a rear rudder plate, the front rudder plate is located at both ends of the front wing, and the rear rudder plate is located at both ends of the rear wing.

8. The multi-state aircraft of claim 7, wherein the forward wing is rotationally provided with a dihedral, the forward rudder plate is rotationally provided with a dihedral, the aft wing is rotationally provided with a dihedral, and the aft rudder plate is rotationally provided with a dihedral.

9. A multi-state aircraft according to claim 8, characterized in that the dihedral and the dihedral are each provided with an opening adapted to the front and rear rudder plates.

10. The multi-modal aircraft of claim 1, wherein the front wing and the rear wing are provided with rollers.

Images