CN114802708A

CN114802708A - Novel automatic unfolding structure of aircraft fixed wing and rudder wing

Info

Publication number: CN114802708A
Application number: CN202210738500.XA
Authority: CN
Inventors: 刘福祥; 李峻恺; 莫波
Original assignee: Beijing Institute of Technology BIT
Current assignee: Beijing Institute of Technology BIT
Priority date: 2022-06-28
Filing date: 2022-06-28
Publication date: 2022-07-29
Anticipated expiration: 2042-06-28
Also published as: CN114802708B

Abstract

The invention discloses a novel automatic unfolding structure of an aircraft fixed wing and a rudder wing, belonging to the technical field of aircrafts; the utility model provides a novel automatic expandes structure of aircraft stationary vane and rudder wing, includes: a body; a wing component comprising a fixed wing flap and a rudder wing flap; further comprising: a rotating component comprising a connecting plate, a fixed-wing airfoil seat, and a first pin; the limiting component comprises a first clamping block, a second clamping block and a convex tooth, the convex tooth is fixedly arranged on the upper surface of the first clamping block, a groove is formed in the lower surface of the second clamping block, a first torsion spring is sleeved at the bottom end of the first pin rod, and a first stopping block is fixedly arranged at the bottom end of the first pin rod; the invention effectively solves the problems that the common fixed wing and rudder wing lateral folding and unfolding mechanism of the existing aircraft occupies large space, is not accurate in unfolding position, and is difficult to meet the use requirements of large unfolding moment and large bending moment.

Description

Novel automatic unfolding structure of aircraft fixed wing and rudder wing

Technical Field

The invention relates to the technical field of aircrafts, in particular to a novel automatic unfolding structure of an aircraft fixed wing and a rudder wing.

Background

Unmanned aerial vehicle is a new thing that appears along with the continuous development of society, and the wing of unmanned aerial vehicle on the existing market divide into rotor and fixed wing, and in order to make things convenient for unmanned aerial vehicle's to carry, in the prior art, usually can make the optimization in the aspect of the structure of wing for the wing forms collapsible mode, when using, can expand, in the non-use stage, can fold the wing.

The existing lateral folding and unfolding mechanism for the common fixed wing and the rudder wing of the aircraft has the disadvantages of large occupied space, inaccurate unfolding position, complex installation, high processing difficulty, limited aircraft space, large unfolding moment, high requirement for bearing large bending moment and the like, and is difficult to meet the requirement in complex application scenes.

Disclosure of Invention

The invention aims to provide a novel automatic unfolding structure of an aircraft fixed wing and a rudder wing, which aims to solve the problems in the background technology:

The utility model provides a novel automatic expandes structure of aircraft stationary vane and rudder wing, includes:

a body having a cylindrical shape;

the wing component is vertically arranged on the outer side of the machine body and comprises a fixed wing fin and a rudder wing fin;

further comprising:

the rotating component comprises a connecting plate, a fixed wing seat and a first pin rod, the connecting plate is vertically and fixedly attached to the outer side of the machine body, the fixed wing seat is fixedly installed on the side face of the connecting plate, and the top end of the first pin rod is vertically sleeved in the fixed wing seat and rotates and vertically slides in the fixed wing seat;

the limiting component comprises a first clamping block, a second clamping block and a convex tooth, the first clamping block is horizontally and fixedly installed on the outer side surface of the connecting plate, the second clamping block is fixedly connected with the side surface of the fixed wing fin, the first clamping block is movably sleeved with the first pin rod, the second clamping block is fixedly sleeved with the first pin rod, the convex tooth is fixedly installed on the upper surface of the first clamping block, a groove is formed in the lower surface of the second clamping block, the convex tooth is matched with the groove, a first torsion spring is sleeved at the bottom end of the first pin rod, a first stopping block is fixedly installed at the bottom end of the first pin rod, and the bottom end of the first torsion spring is vertical and is fixedly inserted in the first stopping block;

a deflection component for driving the rudder wing fin to swing.

The unfolding and folding of rudder wing fin are realized, simultaneously, it is guaranteed that in the flying process, the rudder wing fin is controllable and preferable, the deflection component comprises a rudder wing seat and a sleeve, the sleeve is fixedly installed on the side face of the rudder wing seat, a second pin rod is sleeved on the inner portion of the sleeve in a perpendicular and movable mode, a second torsion spring is sleeved at the bottom end of the second pin rod, a second stop block is fixedly installed at the bottom end of the second pin rod, the bottom end of the second torsion spring is vertical and is fixedly inserted into the second stop block, a limiting component is arranged on the second pin rod, a first clamping block in the limiting component on the second pin rod is fixedly connected with the rudder wing seat, a second clamping block in the limiting component on the second pin rod is fixedly connected with the side face of the rudder wing fin, the first clamping block is movably sleeved with the second pin rod, and the second clamping block is fixedly sleeved with the second pin rod.

The wing parts are efficiently limited, preferably, the number of the limiting parts on the first pin rod is three, the number of the limiting parts on the second pin rod is two, the side face of the machine body is vertically provided with a placing face, the placing face is a plane, and the placing face is used for placing the wing parts after being folded.

The rotation of realization rudder wing fin is controlled the gesture of organism, preferred, still includes the steering wheel, steering wheel fixed mounting is on the organism, and the output shaft passes through the switching part and is connected with rudder wing seat.

The connection between the wing seat of the rudder wing and the output shaft of the steering engine is controlled, the transmission and the disconnection of the torque are realized, preferably, the switching component comprises a connecting rod, a supporting block, a shaft sleeve, two first limiting blocks, two second limiting blocks and two third limiting blocks, an inner cavity is arranged in the supporting block, the connecting rod and the output shaft of the steering engine are respectively vertically and rotatably sleeved at the upper end and the lower end of the supporting block, one ends close to each other are respectively penetrated into the inner cavity, the shaft sleeve is positioned in the inner cavity and is sleeved on the connecting rod in a sliding manner, limiting cavities are vertically and symmetrically arranged in the shaft sleeve, the two first limiting blocks are respectively positioned in the two limiting cavities and are respectively and fixedly connected with the outer side of the connecting rod, the two second limiting blocks are symmetrically and vertically and fixedly arranged at the top end of the shaft sleeve, two first clamping grooves are symmetrically and vertically arranged on the top wall of the inner cavity, and are respectively matched with the two second limiting blocks, two third stopper symmetry fixed mounting has seted up the second draw-in groove perpendicularly in the steering wheel output shaft outside, the second draw-in groove matches with two third stoppers, be equipped with adjusting part in the bracer, adjusting part is used for adjusting the height of axle sleeve, connecting rod top and rudder wing seat fixed connection.

Be convenient for order about axle sleeve lift and location, it is preferred, regulating part includes carousel, slider, screw rod and guide rail, the fixed cup joint of carousel is on the axle sleeve, the arrangement groove has been seted up to the inner chamber lateral wall, the perpendicular fixed mounting of guide rail is at arrangement groove lateral wall, the spout has been seted up in the carousel outside, slider slidable mounting is on the guide rail, and slides and inlay and establish in the spout, the screw rod is rotated the cover perpendicularly and is established in the vaulting pole, and runs through the arrangement groove, slider threaded sleeve establishes on the screw rod.

Advantageous effects

Compared with the prior art, the invention has the advantages that:

(1) the invention realizes the limitation of the folding and unfolding of the wing parts through the multi-stage limiting parts, and occupies smaller space;

(2) according to the invention, the convex teeth are meshed with the grooves, so that the wing parts can be accurately unfolded in place, and a larger bending moment and a larger hinge moment are borne;

(3) the invention can realize the combination and the separation of the rudder wing seat and the rudder wing output shaft through the adapter part, transmits the torque to the rudder wing fin during the flight, and breaks the connection between the rudder wing output shaft and the rudder wing fin during the folding, thereby avoiding transmitting the torque to the rudder wing when the rudder wing fin is pulled and preventing the rudder wing from being damaged.

Drawings

Fig. 1 is a schematic perspective view of a novel auto-unfolding structure of an aircraft fixed wing and a rudder wing according to the present invention in an unfolded state;

fig. 2 is a schematic perspective view of a novel automatic unfolding structure of an aircraft fixed wing and a rudder wing provided by the present invention in a retracted state;

FIG. 3 is a schematic perspective view of a fixed wing flap in an extended state in an automatically extended structure of a new type of aircraft fixed wing and rudder wing according to the present invention;

FIG. 4 is a schematic perspective view of a rudder wing panel in an unfolded state in a novel auto-unfolding structure of an aircraft fixed wing and a rudder wing according to the present invention;

fig. 5 is a schematic perspective view of a wing member in a retracted state in a novel automatic deployment structure of an aircraft fixed wing and a rudder wing according to the present invention;

FIG. 6 is a schematic perspective view of a transfer unit in an auto-deployment structure of a novel fixed wing and a rudder wing of an aircraft according to the present invention;

FIG. 7 is a schematic structural view of a front cross-section of a strut block in an automatically deployed structure of a novel fixed wing and a rudder wing of an aircraft according to the present invention;

fig. 8 is a schematic perspective sectional structure view of the shaft sleeve in the novel automatic unfolding structure of the fixed wing and the rudder wing of the aircraft according to the present invention.

The reference numbers in the figures illustrate: 1. a body; 2. a fixed-wing airfoil; 3. rudder wing panels; 4. a connecting plate; 5. a fixed-wing seat; 6. a first pin rod; 7. a first clamping block; 8. a second fixture block; 9. a convex tooth; 10. a groove; 11. a first torsion spring; 12. a first stopper; 13. a rudder wing seat; 14. a sleeve; 15. a second pin; 16. a second torsion spring; 17. a second stopper; 18. placing the noodles; 19. a steering engine; 20. a connecting rod; 21. a support block; 22. a shaft sleeve; 23. a first stopper; 24. a second limiting block; 25. a third limiting block; 26. an inner cavity; 27. a limiting cavity; 28. a first card slot; 29. a second card slot; 30. a turntable; 31. a slider; 32. a screw; 33. a guide rail; 34. a placing groove; 35. a chute; 36. a hand wheel; 37. an elastic washer.

Detailed Description

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the equipment or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.

In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted", "provided", "fitted/connected", "connected", and the like, are to be interpreted broadly, such as "connected", which may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

Example 1:

referring to fig. 1 to 8, a novel automatic unfolding structure for fixed wings and rudder wings of an aircraft includes:

the machine body 1 is cylindrical;

the aircraft comprises wing components, wherein the wing components are arranged in multiple groups, the multiple groups of wing components are symmetrically and vertically arranged on the outer side of an aircraft body 1, and each wing component comprises a fixed wing fin 2 and a rudder wing fin 3;

further comprising:

the rotating component comprises a connecting plate 4, a fixed wing seat 5 and a first pin rod 6, wherein the connecting plate 4 is vertically and fixedly attached to the outer side of the machine body 1, the fixed wing seat 5 is fixedly arranged on the side surface of the connecting plate 4, and the top end of the first pin rod 6 is vertically sleeved in the fixed wing seat 5 and rotates and vertically slides in the fixed wing seat 5;

the limiting component comprises a first clamping block 7, a second clamping block 8 and a convex tooth 9, the first clamping block 7 is horizontally and fixedly installed on the outer side surface of the connecting plate 4, the second clamping block 8 is fixedly connected with the side surface of the fixed wing piece 2, the first clamping block 7 is movably sleeved with the first pin rod 6, the second clamping block 8 is fixedly sleeved with the first pin rod 6, the convex tooth 9 is fixedly installed on the upper surface of the first clamping block 7, a groove 10 is formed in the lower surface of the second clamping block 8, the convex tooth 9 is matched with the groove 10, a first torsion spring 11 is sleeved at the bottom end of the first pin rod 6, a first stop block 12 is fixedly installed at the bottom end of the first pin rod 6, the bottom end of the first torsion spring 11 is vertical and is fixedly inserted in the first stop block 12;

a deflection component for driving the rudder wing fin 3 to swing.

The deflection component comprises a rudder wing seat 13 and a sleeve 14, the sleeve 14 is fixedly installed on the side face of the rudder wing seat 13, a second pin rod 15 is vertically movably sleeved inside the sleeve, a second torsion spring 16 is sleeved at the bottom end of the second pin rod 15, a second stopper 17 is fixedly installed at the bottom end of the second pin rod 15, the bottom end of the second torsion spring 16 is vertical and is fixedly inserted in the second stopper 17, a limiting component is arranged on the second pin rod 15, a first fixture block 7 in the limiting component on the second pin rod 15 is fixedly connected with the rudder wing seat 13, a second fixture block 8 in the limiting component on the second pin rod 15 is fixedly connected with the side face of the rudder wing fin 3, the first fixture block 7 is movably sleeved with the second pin rod 15, and the second fixture block 8 is fixedly sleeved with the second pin rod 15.

The limiting parts on the first pin rod 6 are three groups, the limiting parts on the second pin rod 15 are two groups, the placing surface 18 is vertically arranged on the side surface of the machine body 1, the placing surface 18 is a plane, the placing surface 18 is used for placing the wing parts after being folded, the wing parts are wound and fixed through the binding bands after being folded, the two ends of the binding bands are fixed through the pin pulling device, a ring body is formed, and the wing parts are prevented from rebounding.

According to the requirements of bending moment and torque required to be borne by wing components, bending moment and torque which can be borne can be increased by increasing more stages of convex teeth 9 and grooves 10, in the scheme, three stages are selected for controlling the fixed wing fins 2, and two stages are selected for controlling the rudder wing fins 3.

When flying, the fixed wing 2 and the rudder wing 3 are both in an unfolded state, at this time, the convex teeth 9 are meshed with the grooves 10 to form a clamping structure, in the flying process, even if the fixed wing 2 and the rudder wing 3 are stressed in the flying process, the convex teeth 9 are meshed with the grooves 10, if the fixed wing 2 and the rudder wing 3 want to deflect, the second fixture block 8 needs to be driven to rotate, because the first fixture block 7 is fixed, the convex teeth 9 are fixed, the second fixture block 8 rotates, the grooves 10 are separated from the convex teeth 9, because the convex teeth 9 are matched with the grooves 10, the deflection of wing parts is blocked, and because of the existence of the first torsion spring 11 and the second torsion spring 16, the meshing effect of the convex teeth 9 and the grooves 10 is realized, the separation of the convex teeth 9 and the grooves 10 is avoided, the adhesion of trapezoidal contact surfaces is ensured, and the fixed wing 2 and the rudder wing 3 are kept relatively static relative to the fixed wing seat 5 and the rudder wing seat 13, the bending moment and the hinge moment generated by airflow can be borne to the maximum extent.

When the wing part needs to be folded, the fixed wing 2 and the rudder wing 3 are manually pulled, the fixed wing 2 drives the first pin 6, the first torsion spring 11 and the three second fixture blocks 8 to rotate, the second fixture blocks 8 rotate, the grooves 10 are disengaged from the convex teeth 9, the first pin 6 moves upwards to compress the first torsion spring 11, the first torsion spring 11 deforms to generate elastic force, when the convex teeth 9 are disengaged from the grooves 10 and the convex teeth 9 are in plane contact with the bottom of the second fixture blocks 8, the convex teeth 9 are tightly pressed on the bottom surface of the second fixture blocks 8 under the elastic force of the first torsion spring 11, the fixed wing 2 is prevented from being unfolded, when the rudder wing part 3 is pulled, the rudder wing part 3 is also folded and positioned outside the machine body 1 under the action of the second torsion spring 16, when the wing part needs to be unfolded again, the convex teeth 9 are engaged with the grooves 10, can realize the expansion of stationary vane wing 2 and rudder wing fin 3 fixed, guarantee to expand accurate target in place, also effectively avoid simultaneously to bounce and cross and kick-back.

The wing parts can be folded and unfolded in the mode, the space size occupied by the folding and unfolding structure is effectively reduced, the positioning accuracy of the unfolding of the wing parts is improved due to the meshing design of the convex teeth 9 and the grooves 10, and the bending moment and the hinge moment which can be borne by the wing parts are improved due to multi-stage meshing.

Example 2:

referring to fig. 1 to 8, the difference from embodiment 1 is that the rudder wing aircraft further includes a steering engine 19, the steering engine 19 is fixedly installed on the aircraft body 1, and the output shaft is connected with the rudder wing base 13 through an adapter.

The adapter part comprises a connecting rod 20, a supporting block 21, a shaft sleeve 22, two first limiting blocks 23, two second limiting blocks 24 and two third limiting blocks 25, the supporting block 21 is fixedly connected with the machine body 1, an inner cavity 26 is formed in the supporting block 21, the connecting rod 20 and a steering engine output shaft 19 are respectively vertically sleeved at the upper end and the lower end of the supporting block 21 in a rotating mode, one ends close to each other penetrate into the inner cavity 26, the shaft sleeve 22 is positioned in the inner cavity 26 and is sleeved on the connecting rod 20 in a sliding mode, limiting cavities 27 are vertically and symmetrically formed in the shaft sleeve 22, the two first limiting blocks 23 are respectively positioned in the two limiting cavities 27 and are fixedly connected with the outer side of the connecting rod 20, the two second limiting blocks 24 are symmetrically and vertically fixedly installed at the top end of the shaft sleeve 22, two first clamping grooves 28 are symmetrically and vertically formed in the top wall of the inner cavity 26, the two first clamping grooves 28 are respectively matched with the two second limiting blocks 24, and the two third limiting blocks 25 are symmetrically and fixedly installed on the outer side of the steering engine output shaft 19, a second clamping groove 29 is vertically formed in the bottom surface of the shaft sleeve 22, the second clamping groove 29 is matched with the two third limiting blocks 25, an adjusting part is arranged in the supporting block 21 and used for adjusting the height of the shaft sleeve 22, and the top end of the connecting rod 20 is fixedly connected with the rudder wing seat 13.

The adjusting part comprises a rotary disc 30, a sliding block 31, a screw rod 32 and a guide rail 33, the rotary disc 30 is fixedly sleeved on the shaft sleeve 22, a mounting groove 34 is formed in the side wall of the inner cavity 26, the guide rail 33 is vertically and fixedly mounted on the side wall of the mounting groove 34, a sliding groove 35 is formed in the outer side of the rotary disc 30, the sliding block 31 is slidably mounted on the guide rail 33 and is slidably embedded in the sliding groove 35, the screw rod 32 is vertically rotatably sleeved in the supporting block 21 and penetrates through the mounting groove 34, the sliding block 31 is in threaded sleeve connection with the screw rod 32, the bottom of the screw rod 32 penetrates out of the bottom of the supporting block 21 and is fixedly sleeved with a hand wheel 36, an elastic gasket 37 is fixedly attached to the bottom of the supporting block 21, the elastic gasket 37 is sleeved on the screw rod 32 and is in sliding contact with the hand wheel 36, the hand wheel 36 is convenient for rotating the screw rod 32, and the elastic gasket 37 can prevent the screw rod 32 from rotating independently.

In the flying process, the shaft sleeve 22 is located at the lowest limit position, at this time, the two third limiting blocks 25 are located in the second clamping grooves 29, the two second limiting blocks 24 are respectively separated from the two first clamping grooves 28, when the output shaft of the steering engine 19 rotates, the two third limiting blocks 25 rotate to drive the shaft sleeve 22 to rotate, the shaft sleeve 22 drives the two first limiting blocks 23 to rotate through the two limiting cavities 27, as the two first limiting blocks 23 are fixedly connected with the connecting rod 20, the connecting rod 20 rotates, the connecting rod 20 drives the rudder wing seat 13 to rotate, the torsion of the steering engine 19 is transmitted to the rudder wing 3, when the rudder wing 3 needs to be folded, the steering engine 19 returns to zero, the hand wheel 36 is rotated, the hand wheel 36 drives the screw rod 32 to rotate, the screw rod 32 drives the slide block 31 to move upwards on the guide rail 33, the slide block 31 slides upwards to drive the rotary disc 30 to move upwards, the rotary disc 30 drives the shaft sleeve 22 to move upwards, make second draw-in groove 29 and two third stopper 25 break away from, along with axle sleeve 22's continuous rising, two second stopper 24 insert two first draw-in grooves 28 respectively, realize the joint, when pulling rudder wing fin 3, because two first draw-in grooves 28 and two second stopper 24, and the interference of two spacing chambeies 27 and two first stopper 23, connecting rod 20 can the stillness, thereby be convenient for pulling of rudder wing fin 3, and simultaneously, because axle sleeve 22 bottom breaks away from with steering wheel 19 output shaft top, thereby make connecting rod 20's torsion can not transmit steering wheel 19 output shaft for, when avoiding pulling rudder wing fin 3, cause the damage to steering wheel 19.

When the flying vehicle needs to fly, the hand wheel 36 is rotated reversely, so that the shaft sleeve 22 descends and is clamped with the two third limiting blocks 25 again.

The foregoing shows and describes the general principles, essential features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and the preferred embodiments of the present invention are described in the above embodiments and the description, and are not intended to limit the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.

Claims

1. The utility model provides a novel automatic expandes structure of aircraft stationary vane and rudder wing, includes:

a machine body (1), wherein the machine body (1) is cylindrical;

the wing component is vertically arranged on the outer side of the machine body (1) and comprises a fixed wing fin (2) and a rudder wing fin (3);

it is characterized by also comprising:

the rotating component comprises a connecting plate (4), a fixed wing seat (5) and a first pin rod (6), the connecting plate (4) is vertically and fixedly attached to the outer side of the machine body (1), the fixed wing seat (5) is fixedly installed on the side face of the connecting plate (4), and the top end of the first pin rod (6) is vertically sleeved in the fixed wing seat (5) and rotates and vertically slides in the fixed wing seat (5);

the limiting component comprises a first clamping block (7), a second clamping block (8) and a convex tooth (9), the first clamping block (7) is horizontally and fixedly installed on the outer side surface of the connecting plate (4), the second clamping block (8) is fixedly connected with the side surface of the fixed wing piece (2), the first clamping block (7) is movably sleeved with the first pin rod (6), the second clamping block (8) is fixedly sleeved with the first pin rod (6), the convex tooth (9) is fixedly installed on the upper surface of the first clamping block (7), a groove (10) is formed in the lower surface of the second clamping block (8), the convex tooth (9) is matched with the groove (10), a first torsion spring (11) is sleeved at the bottom end of the first pin rod (6), a first stop block (12) is fixedly installed at the bottom end of the first pin rod (6), the bottom end of the first torsion spring (11) is vertical, and is fixedly inserted in the first stop block (12);

a deflection component for driving the rudder wing fin (3) to swing.

2. The novel automatic unfolding structure of the fixed wing and the rudder wing of the aircraft according to claim 1, is characterized in that: the deflection component comprises a rudder wing seat (13) and a sleeve (14), the sleeve (14) is fixedly arranged on the side surface of the rudder wing seat (13), a second pin rod (15) is vertically and movably sleeved inside, a second torsion spring (16) is sleeved at the bottom end of the second pin rod (15), a second stop block (17) is fixedly arranged at the bottom end of the second pin rod (15), the bottom end of the second torsion spring (16) is vertical, and is fixedly inserted in a second stop block (17), a limiting part is arranged on the second pin rod (15), a first clamping block (7) in the upper limiting part of the second pin rod (15) is fixedly connected with the wing seat (13) of the rudder wing, a second fixture block (8) in the upper limiting part of the second pin rod (15) is fixedly connected with the side surface of the rudder wing fin (3), the first fixture block (7) is movably sleeved with the second pin rod (15), and the second fixture block (8) is fixedly sleeved with the second pin rod (15).

3. The novel automatic unfolding structure of the fixed wing and the rudder wing of the aircraft according to claim 2, is characterized in that: the limiting components on the first pin rod (6) are three groups, the limiting components on the second pin rod (15) are two groups, the side face of the machine body (1) is perpendicularly provided with a placement face (18), the placement face (18) is a plane, and the placement face (18) is used for placing the wing components after being folded.

4. The novel automatic unfolding structure of the fixed wing and the rudder wing of the aircraft according to claim 1, is characterized in that: the wing rudder is characterized by further comprising a steering engine (19), wherein the steering engine (19) is fixedly installed on the machine body (1), and an output shaft is connected with the wing base (13) of the rudder wing through a switching component.

5. The novel automatic unfolding structure of the fixed wing and the rudder wing of the aircraft as claimed in claim 4, wherein: the adapter part comprises a connecting rod (20), a supporting block (21), a shaft sleeve (22), two first limiting blocks (23), two second limiting blocks (24) and two third limiting blocks (25), an inner cavity (26) is formed in the supporting block (21), the connecting rod (20) and an output shaft of a steering engine (19) are respectively vertically and rotatably sleeved at the upper end and the lower end of the supporting block (21), one ends close to each other penetrate into the inner cavity (26), the shaft sleeve (22) is positioned in the inner cavity (26) and is sleeved on the connecting rod (20) in a sliding manner, limiting cavities (27) are vertically and symmetrically formed in the shaft sleeve (22), the two first limiting blocks (23) are respectively positioned in the two limiting cavities (27) and are fixedly connected with the outer side of the connecting rod (20), the two second limiting blocks (24) are symmetrically and vertically and fixedly installed at the top end of the shaft sleeve (22), two first clamping grooves (28) are symmetrically and vertically formed in the top wall of the inner cavity (26), two first draw-in groove (28) respectively with two second stopper (24) phase-matchs, two third stopper (25) symmetry fixed mounting is in steering wheel (19) output shaft outside, second draw-in groove (29) have been seted up perpendicularly to axle sleeve (22) bottom surface, second draw-in groove (29) and two third stopper (25) phase-matchs, be equipped with adjusting part in brace (21), adjusting part is used for adjusting the height of axle sleeve (22), connecting rod (20) top and rudder wing seat (13) fixed connection.

6. The novel automatic unfolding structure of the fixed wing and the rudder wing of the aircraft as claimed in claim 5, wherein: the adjusting part comprises a rotary table (30), a sliding block (31), a screw rod (32) and a guide rail (33), the rotary table (30) is fixedly sleeved on a shaft sleeve (22), a mounting groove (34) is formed in the side wall of the inner cavity (26), the guide rail (33) is vertically and fixedly installed on the side wall of the mounting groove (34), a sliding groove (35) is formed in the outer side of the rotary table (30), the sliding block (31) is slidably installed on the guide rail (33) and is slidably embedded in the sliding groove (35), the screw rod (32) is vertically sleeved in a supporting block (21) in a rotating mode and penetrates through the mounting groove (34), and the sliding block (31) is sleeved on the screw rod (32) in a threaded mode.