Aircraft structure with wing folding and empennage swinging functions

Abstract

The invention provides an aircraft structure with wing folding and empennage swinging functions, and relates to the technical field of aircraft structures, the aircraft structure comprises two fixing blocks, and the two fixing blocks are fixedly connected to the rear end of a fuselage rod; the number of the mounting sliding grooves is two, and the two mounting sliding grooves are formed in the inner sides of the two fixing blocks correspondingly. The fixed wing is mounted at the front end of the fuselage rod; the mounting cylinder is fixedly connected to the lower end face of the fixed wing, and the mounting cylinder is slidably connected to the front end of the fuselage rod; the number of the fastening bolts is two, and the two fastening bolts are both in threaded connection with the inner side of the mounting cylinder, so that the problem that in the flying process of an existing remote control aircraft structure, when an aircraft accidentally falls to the ground due to inaccurate and appropriate control, an empennage of the aircraft is prone to being damaged or even fractured is solved; and as the empennage of the remote control aircraft is mostly fixedly mounted on the fuselage, the replacement of the empennage is troublesome, and the flight efficiency is improved.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft structures, and in particular to an aircraft structure with wing folding and tail swinging functions. Background Art

[0002] An airplane is an aircraft that can fly in the air, while a remote-controlled airplane is an aircraft that can be controlled from a distance by a remote control. The remote-controlled airplane relies on a receiver equipped on the aircraft to receive the radio signals transmitted by the remote control, decode them into corresponding commands, and then pass them to the aircraft's internal servos to control the aircraft's flight attitude and realize flight operations.

[0003] According to the application number: CN200320119026.5, a single-chip microcomputer controlled electric remote control aircraft is disclosed, which includes a battery, an elevator steering gear, a connecting rod, a propeller, a landing gear, a fuselage, a main wing, a horizontal tail, and a vertical tail. The invention is characterized in that: there is also a single-chip microcomputer control circuit, a left motor, and a right motor, the left motor and the right motor are symmetrically installed on both sides of the fuselage, the propellers are respectively installed on the rotating shafts of the left motor and the right motor, the elevator steering gear is connected to the elevator surface of the horizontal tail through the connecting rod, and the control signal output by the single-chip microcomputer control circuit is respectively sent to the left motor, the right motor and the elevator steering gear. Due to the use of a programmable single-chip microcomputer for signal processing, a control effect that is difficult to achieve with a traditional analog circuit is achieved, and a dual-motor proportional speed control steering gear control device is used to replace the control device used in a traditional three-channel proportional remote control model aircraft, which reduces the cost, is easy to manufacture, has a wide range of applications, and is conducive to the development of the model aircraft industry.

[0004] According to the application number: CN201710684839.5, a fixed-wing vector drone is disclosed, which has a fuselage, a steering gear, a flight control system, a propeller and a brushless motor. The fuselage is composed of a wing plate and upper and lower fuselage side plates. A motor fixing seat is fixed at the front end of the fuselage. A rotating support ring is installed on the motor fixing seat through a rotating bracket. The rotating support ring rotates around its radial axis. A cross rotating bracket is installed in the rotating support ring. A brushless motor is installed on the cross rotation. A propeller is installed on the brushless motor shaft. A left and right deflection steering gear and an up and down deflection steering gear are installed in the fuselage. Each steering gear is connected to the rotating support ring and the cross rotating bracket respectively through a ball head pull rod to control the deflection of the propeller and the brushless motor axis. The flight control system includes a remote control ground remote controller, a remote control receiver on the fuselage and an APM flight controller, and the flight control system is electrically connected to the left and right deflection steering gear and the up and down deflection steering gear. The vector of the present invention can rotate adaptively, provide timely pulling force for different actions, reduce the aircraft's take-off and grounding speed, shorten the aircraft's taxiing distance, and save power consumption.

[0005] However, with the existing remote-controlled aircraft structure, when the aircraft accidentally falls to the ground due to inaccurate control or aircraft malfunction during flight, the tail of the aircraft is often easily damaged or even broken. Since the tail of the remote-controlled aircraft is mostly fixed to the fuselage, this fixing method makes it more troublesome to replace the tail once it is damaged, which will have an adverse effect on the subsequent flight efficiency and is not conducive to the normal development of flight activities. Summary of the invention

[0006] In view of this, the present invention provides an aircraft structure with wing folding and tail swinging functions, which has the advantages of improving flight efficiency and reducing labor intensity.

[0007] The present invention provides an aircraft structure with wing folding and tail wing swinging functions, which specifically includes a fuselage rod, a fixing block, an installation slide groove, a fixed wing, a mounting barrel, fastening bolts, a cabin, a cabin cover, a receiver, a steering gear, a control rod, a battery installation mechanism, an aircraft propulsion mechanism and an aircraft control mechanism; two fixing blocks are provided, and the two fixing blocks are fixedly connected to the rear end of the fuselage rod; two installation slide grooves are provided, and the two installation slide grooves are respectively opened on the inner sides of the two fixing blocks; the fixed wing is installed at the front end of the fuselage rod; the mounting barrel is fixedly connected to the lower end surface of the fixed wing, and the mounting barrel slide is fixedly connected to the lower end surface of the fixed wing. The invention relates to a frame structure of the present invention that is dynamically connected to the front end of the fuselage rod; there are two fastening bolts, both of which are threadedly connected to the inner side of the mounting tube; the cabin is plugged and installed at the front end of the fuselage rod; the cabin cover is installed at the upper end of the cabin; the receiver is fixedly installed on the inner side of the cabin; there are two servos, both of which are fixedly installed on the inner side of the cabin; there are two control rods, both of which are fixedly installed on the upper ends of the two servo shafts; the battery mounting mechanism is arranged on the inner side of the cabin; the aircraft propulsion mechanism is arranged at the rear end of the cabin; the aircraft control mechanism is arranged at the upper end of the cabin.

[0008] Furthermore, the battery installation mechanism includes: a positioning rod, a positioning block, a mounting joint, a positioning groove, a battery box and a battery block; the positioning rods are provided with two, and the two positioning rods are fixedly connected to the inner side of the cabin; the positioning blocks are provided with two, and the two positioning blocks are respectively fixedly connected to the upper ends of the two positioning rods; the mounting joint is hinged on the inner side of the cabin; the positioning grooves are provided with two, and the two positioning grooves are opened on the outer side of the mounting joint; the battery box is plugged into the inner side of the mounting joint; the battery block is installed on the inner side of the battery box.

[0009] Furthermore, the aircraft propulsion mechanism includes: a propulsion cylinder, a sliding plate, a fixed plate and a compression spring; the propulsion cylinder is fixedly connected to the upper end of the rear end of the cabin; the sliding plate is slidably connected to the inner side of the propulsion cylinder; the fixed plate is fixedly connected to the front end surface of the sliding plate; the front end of the compression spring is fixedly connected to the inner side of the propulsion cylinder, and the rear end of the compression spring is fixedly connected to the front end surface of the sliding plate.

[0010] Furthermore, the aircraft propulsion mechanism also includes: a limit slider, a limit spring and a first connecting rope; the limit slider is slidably connected to the inner side of the propulsion cylinder, and the limit slider is inserted into the inner side of the fixed plate; the upper end of the limit spring is fixedly connected to the lower end surface of the limit slider, and the lower end of the limit spring is fixedly connected to the inner side of the propulsion cylinder; the upper end of the first connecting rope is fixedly connected to the lower end surface of the limit slider, and the lower end of the first connecting rope is fixedly connected to the outer side of the rear end control rod.

[0011] Furthermore, the aircraft control mechanism includes: folding wings and elastic members; the folding wings are provided with two, and both folding wings are hinged on the outside of the fixed wings; the elastic members are provided with two groups, and the two ends of the two groups of elastic members are respectively fixedly connected to the upper end surfaces of the fixed wings and the folding wings.

[0012] Furthermore, the aircraft control mechanism also includes: an articulated rod and a second connecting rope; there are two articulated rods, and both articulated rods are hinged on the outside of the mounting tube; there are two second connecting ropes, and the front ends of the two second connecting ropes are respectively fixedly connected to the outsides of the two control rods, and the rear ends of the two second connecting ropes are respectively fixedly connected to the outsides of the two articulated rods.

[0013] Furthermore, the aircraft control mechanism also includes: an installation tail, an installation slider, a steering tail, a connecting block and a connecting slide; the installation tail is provided with two, and the two installation tails are respectively installed on the outside of the two fixed blocks; the installation slider is provided with two, and the two installation sliders are respectively fixedly connected to the outside of the two installation tails, and the two installation sliders are respectively slidably connected to the two installation slides; the steering tail is provided with two, and the two steering tails are respectively hinged at the rear ends of the two installation tails; the connecting block is fixedly connected to the upper end surfaces of the two steering tails; the connecting slides are provided with two, and the two connecting slides are respectively opened on the inner sides of the two connecting blocks.

[0014] Furthermore, the aircraft control mechanism also includes: a limit mounting block and a mounting bolt; two limit mounting blocks are provided, and the two limit mounting blocks are respectively slidably connected to the inner sides of the two mounting grooves; two mounting bolts are provided, and the two mounting bolts are respectively threadedly connected to the inner sides of the two fixing blocks.

[0015] Furthermore, the aircraft control mechanism also includes: an adjusting connecting rod; two adjusting connecting rods are provided, the front ends of the two adjusting connecting rods are respectively fixedly connected to the outsides of the two control rods, and the rear ends of the two adjusting connecting rods are respectively slidably connected to the insides of the two connecting slide grooves.

[0016] Beneficial effects:

[0017] The present invention makes the installation of the battery block more convenient through the arrangement of the battery installation mechanism. First, the battery block is placed in the battery box, and then the installation joint is flipped upward. At this time, the positioning block will be against the inner side of the positioning groove under the action of the positioning rod, so as to realize the positioning of the installation joint. Subsequently, the battery box can be inserted into the inner side of the installation joint to complete the installation of the battery block, and finally the installation joint can be reset. The whole operation process is simple and easy, which effectively improves work efficiency.

[0018] In addition, through the setting of the aircraft propulsion mechanism, the purpose of propulsion of the aircraft is achieved. The gunpowder used to propel the aircraft is inserted into the inner side of the propulsion tube, and then the aircraft is placed on the launch pad and the gunpowder is ignited. The combustion of the gunpowder will push the aircraft into the air. When the controller is used to control the servo via the receiver, the rotation of the servo will drive the control rod to rotate accordingly, and the rotation of the control rod will drive the limit slider to slide downward with the help of the first connecting rope, so that the limit slider is separated from the fixed plate. In this way, the sliding plate will slide backward under the action of the compression spring, and then the burned gunpowder will be pushed out. In this way, the weight of the aircraft is reduced and the stable flight of the aircraft is guaranteed.

[0019] In addition, the setting of the aircraft control mechanism facilitates the replacement of aircraft accessories. Before the aircraft is launched, the folding wings are folded down and then limited by the hinged rod. After the aircraft is launched, the rotation of the control rod will pull the hinged rod through the second connecting rope. At this time, the folding wings lose their limit and will be unfolded under the action of the elastic member. Moreover, when the servo drives the control rod to rotate, the control rod can also drive the adjustment connecting rod to slide back and forth. The sliding of the adjustment connecting rod will drive the steering tail to tilt up and down under the action of the sliding connection with the connecting slide groove. With the inclination of the steering tail, the aircraft can be controlled to rise and dive as well as turn left and right. At the same time, the setting of the mounting slide groove and the mounting slider makes the replacement of the mounting tail more convenient and simple to operate, which not only improves the flight efficiency but also reduces the labor intensity.

[0020] In addition, the setting of the above-mentioned mechanism facilitates the installation of the battery block, which not only makes the installation of the battery block more convenient and improves work efficiency, but also realizes the effective propulsion of the aircraft, ensures the stable flight of the aircraft, and facilitates the replacement of aircraft accessories, further improving flight efficiency while reducing labor intensity. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the technical solution of the embodiment of the present invention, the drawings of the embodiment are briefly introduced below.

[0022] The accompanying drawings described below are only related to some embodiments of the present invention, and are not intended to limit the present invention. In the accompanying drawings:

[0023] Figure 1 It is a schematic structural diagram of an aircraft body according to the first embodiment of the present invention.

[0024] Figure 2 It is a structural schematic diagram of the lower end surface of the aircraft according to the first embodiment of the present invention.

[0025] Figure 3 It is a schematic structural diagram of a fastening bolt according to the first embodiment of the present invention.

[0026] Figure 4 It is a schematic structural diagram of a control rod according to the first embodiment of the present invention.

[0027] Figure 5 Embodiment 1 of the present invention Figure 4 Schematic diagram of the structure with a partial enlargement at point A in the middle.

[0028] Figure 6 It is a schematic structural diagram of a sectional view of a cabin according to a second embodiment of the present invention.

[0029] Figure 7 The second embodiment of the present invention Figure 6 Schematic diagram of the structure with a partial enlargement at point B in the middle.

[0030] Figure 8 It is a schematic diagram of the structure of the fixing block of the third embodiment of the present invention.

[0031] Fig. 9 It is a schematic structural diagram of a steering tail wing according to the third embodiment of the present invention.

[0032] Fig.10 It is a structural schematic diagram of the adjusting connecting rod of the third embodiment of the present invention.

[0033] List of reference numerals: 1, fuselage rod; 101, fixing block; 102, mounting slide; 2, fixed wing; 201, mounting cylinder; 202, fastening bolt; 203, folding wing; 204, elastic member; 3, cabin; 301, cabin cover; 302, receiver; 303, positioning rod; 304, positioning block; 305, propulsion cylinder; 306, sliding plate; 307, fixing plate; 308, compression spring; 309, limit slide Block; 310, limit spring; 311, first connecting rope; 4, servo; 401, control rod; 5, installation joint; 501, positioning groove; 6, battery box; 7, battery block; 8, hinged rod; 801, second connecting rope; 9, installation tail; 901, installation slider; 902, steering tail; 903, connecting block; 904, connecting slide; 10, limit installation block; 1001, installation bolt; 11, adjustment connecting rod. DETAILED DESCRIPTION

[0034] Example 1: Please refer to Figure 1-Figure 5 As shown:

[0035] The present invention provides an aircraft structure with wing folding and tail wing swinging functions, comprising a fuselage rod 1, a fixing block 101, an installation slide 102, a fixed wing 2, an installation barrel 201, a fastening bolt 202, a cabin 3, a cabin cover 301, a receiver 302, a steering gear 4, a control rod 401, a battery installation mechanism, an aircraft propulsion mechanism and an aircraft control mechanism; two fixing blocks 101 are provided, and the two fixing blocks 101 are fixedly connected to the rear end of the fuselage rod 1; two installation slides 102 are provided, and the two installation slides 102 are respectively opened on the inner sides of the two fixing blocks 101; the fixed wing 2 is installed at the front end of the fuselage rod 1; the installation barrel 201 is fixedly connected to the fixed wing 2 The lower end surface of the fuselage rod 1 is slidingly connected to the mounting tube 201 at the front end thereof; two fastening bolts 202 are provided, and the two fastening bolts 202 are threadedly connected to the inner side of the mounting tube 201; the cabin 3 is plugged and installed at the front end of the fuselage rod 1; the cabin cover 301 is installed at the upper end of the cabin 3; the receiver 302 is fixedly installed on the inner side of the cabin 3; two servos 4 are provided, and the two servos 4 are fixedly installed on the inner side of the cabin 3; two control rods 401 are provided, and the two control rods 401 are respectively fixedly installed on the upper ends of the rotating shafts of the two servos 4; the battery mounting mechanism is arranged on the inner side of the cabin 3; the aircraft propulsion mechanism is arranged at the rear end of the cabin 3; the aircraft control mechanism is arranged at the upper end of the cabin 3.

[0036] Among them, the battery installation mechanism includes: a positioning rod 303, a positioning block 304, a mounting joint 5, a positioning groove 501, a battery box 6 and a battery block 7; there are two positioning rods 303, and the two positioning rods 303 are fixedly connected to the inner side of the cabin 3; there are two positioning blocks 304, and the two positioning blocks 304 are respectively fixedly connected to the upper ends of the two positioning rods 303; the mounting joint 5 is hinged on the inner side of the cabin 3; there are two positioning grooves 501, and the two positioning grooves 501 are both opened on the outer side of the mounting joint 5; the battery box 6 is plugged into the inner side of the mounting joint 5; the battery block 7 is installed on the inner side of the battery box 6.

[0037] The specific usage and function of this embodiment are as follows: after installing the battery block 7 in the battery box 6, the mounting connector 5 is opened upwards. At this time, the positioning block 304 will be pressed against the inner side of the positioning groove 501 under the action of the positioning rod 303 to position the mounting connector 5. At this time, the battery box 6 can be inserted into the inner side of the mounting connector 5 to realize the installation of the battery block 7, and then the mounting connector 5 is reset.

[0038] Embodiment 2: Based on Embodiment 1, Figure 6-Figure 7 As shown, the aircraft propulsion mechanism includes: a propulsion cylinder 305, a sliding plate 306, a fixed plate 307, a compression spring 308, a limit slider 309, a limit spring 310 and a first connecting rope 311; the propulsion cylinder 305 is fixedly connected to the upper end of the rear end of the cabin 3; the sliding plate 306 is slidably connected to the inner side of the propulsion cylinder 305; the fixed plate 307 is fixedly connected to the front end surface of the sliding plate 306; the front end of the compression spring 308 is fixedly connected to the inner side of the propulsion cylinder 305, and the rear end of the compression spring 308 is fixedly connected to the inner side of the propulsion cylinder 305. It is fixedly connected to the front end face of the sliding plate 306; the limit slider 309 is slidably connected to the inner side of the propulsion cylinder 305, and the limit slider 309 is inserted into the inner side of the fixed plate 307; the upper end of the limit spring 310 is fixedly connected to the lower end face of the limit slider 309, and the lower end of the limit spring 310 is fixedly connected to the inner side of the propulsion cylinder 305; the upper end of the first connecting rope 311 is fixedly connected to the lower end face of the limit slider 309, and the lower end of the first connecting rope 311 is fixedly connected to the outer side of the rear end control rod 401.

[0039] The specific usage and function of this embodiment are as follows: insert the gunpowder used to propel the aircraft into the inner side of the propulsion tube 305, then place the aircraft on the launch pad, ignite the gunpowder, the gunpowder will burn for three to five seconds, and push the aircraft into the air. When the controller is used to control the servo 4 through the receiver 302, the servo 4 will drive the control rod 401 to rotate, and the rotation of the control rod 401 will drive the limit slider 309 to slide downward through the first connecting rope 311. At this time, the limit slider 309 will be separated from the fixed plate 307, and the sliding plate 306 will slide backward under the action of the compression spring 308, pushing out the burned gunpowder and reducing the weight of the aircraft.

[0040] Embodiment 3: Based on Embodiment 1, Figure 8-Figure 10 As shown, the aircraft control mechanism includes: a folding wing 203, an elastic member 204, a hinged rod 8, a second connecting rope 801, a mounting tail 9, a mounting slider 901, a steering tail 902, a connecting block 903, a connecting slide 904, a limit mounting block 10, a mounting bolt 1001 and an adjusting connecting rod 11; two folding wings 203 are provided, and the two folding wings 203 are hinged on the outside of the fixed wing 2; two groups of elastic members 204 are provided, and the two ends of the two groups of elastic members 204 are respectively The two hinged rods 8 are respectively fixedly connected to the upper end surfaces of the fixed wing 2 and the folding wing 203; two hinged rods 8 are provided, and the two hinged rods 8 are hinged on the outside of the installation tube 201; two second connecting ropes 801 are provided, and the front ends of the two second connecting ropes 801 are respectively fixedly connected to the outsides of the two control rods 401, and the rear ends of the two second connecting ropes 801 are respectively fixedly connected to the outsides of the two hinged rods 8; two mounting tail wings 9 are provided, and the two mounting tail wings 9 are respectively installed on the outsides of the two fixing blocks 101; There are two mounting slide blocks 901, which are fixedly connected to the outer sides of the two mounting tail wings 9, and the two mounting slide blocks 901 are slidably connected to the two mounting slots 102 respectively; there are two steering tail wings 902, which are hinged at the rear ends of the two mounting tail wings 9; the connecting block 903 is fixedly connected to the upper end surfaces of the two steering tail wings 902; there are two connecting slots 904, which are respectively opened on the inner sides of the two connecting blocks 903; there are two limit mounting blocks 10, which are slidably connected to the inner sides of the two mounting slots 102 respectively; there are two mounting bolts 1001, which are respectively threadedly connected to the inner sides of the two fixed blocks 101; there are two adjusting connecting rods 11, and the front ends of the two adjusting connecting rods 11 are respectively fixedly connected to the outer sides of the two control rods 401, and the rear ends of the two adjusting connecting rods 11 are respectively slidably connected to the inner sides of the two connecting slots 904.

[0041] The specific usage and function of this embodiment are as follows: before launching the aircraft, the folding wings 203 are folded downward, and the hinged rod 8 is used to limit the folding wings 203. When the aircraft is launched, the rotation of the control rod 401 will pull the hinged rod 8 through the second connecting rope 801. At this time, the folding wings 203 lose their limit and will be unfolded under the action of the elastic member 204. The control rod 401 is driven to rotate by the servo 4, so that the control rod 401 drives the adjustment connecting rod 11 to slide forward and backward. The sliding of the adjustment connecting rod 11 will drive the steering tail 902 to tilt up and down under the action of the sliding connection with the connecting slide 904. By tilting the steering tail 902, the control of the aircraft's nose-up dive and left and right steering is realized, and the setting of the mounting slide 102 and the mounting slider 901 facilitates the replacement of the mounting tail 9.

[0042] In this article, there are a few points to note:

[0043] 1. The drawings of the embodiments of the present disclosure only involve structures related to the embodiments of the present disclosure, and other structures may refer to general designs.

[0044] 2. In the absence of conflict, the embodiments of the present disclosure and the features therein may be combined with each other to obtain new embodiments.

[0045] The above are only specific embodiments of the present disclosure, but the protection scope of the present disclosure is not limited thereto. Any technician familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the present disclosure, which should be included in the protection scope of the present disclosure. Therefore, the protection scope of the present disclosure should be based on the protection scope of the claims.

Claims

1. An aircraft structure with wing folding and tail swinging functions, comprising a fuselage rod (1), a fixing block (101), a mounting slot (102), a fixing wing (2), a mounting tube (201), a fastening bolt (202), a cabin (3), a cabin cover (301), a receiver (302), a steering gear (4), a control rod (401), a battery mounting mechanism, an aircraft propulsion mechanism and an aircraft control mechanism; two fixing blocks (101) are provided, and the two fixing blocks (101) are fixedly connected to the rear end of the fuselage rod (1); two mounting slots (102) are provided, and the two mounting slots (102) are respectively opened on the inner sides of the two fixing blocks (101); the characteristics are: The fixed wing (2) is mounted on the front end of the fuselage rod (1); the mounting tube (201) is fixedly connected to the lower end surface of the fixed wing (2), and the mounting tube (201) is slidably connected to the front end of the fuselage rod (1); two fastening bolts (202) are provided, and the two fastening bolts (202) are both threadedly connected to the inner side of the mounting tube (201); the cabin (3) is plugged and mounted on the front end of the fuselage rod (1); the cabin cover (301) is mounted on the upper end of the cabin (3); The receiver (302) is fixedly mounted on the inner side of the cabin (3); two steering gears (4) are provided, and both steering gears (4) are fixedly mounted on the inner side of the cabin (3); two control rods (401) are provided, and both control rods (401) are fixedly mounted on the upper ends of the rotating shafts of the two steering gears (4); the battery mounting mechanism is arranged on the inner side of the cabin (3); the aircraft propulsion mechanism is arranged at the rear end of the cabin (3); and the aircraft control mechanism is arranged at the upper end of the cabin (3).

2. An aircraft structure with wing folding and tail swinging functions as claimed in claim 1, characterized in that: The battery installation mechanism comprises: a positioning rod (303), a positioning block (304), a mounting joint (5), a positioning groove (501), a battery box (6) and a battery block (7); two positioning rods (303) are provided, and the two positioning rods (303) are fixedly connected to the inner side of the cabin (3); two positioning blocks (304) are provided, and the two positioning blocks (304) are respectively fixedly connected to the upper ends of the two positioning rods (303); the mounting joint (5) is hinged to the inner side of the cabin (3); two positioning grooves (501) are provided, and the two positioning grooves (501) are both opened on the outer side of the mounting joint (5); the battery box (6) is plugged into the inner side of the mounting joint (5); and the battery block (7) is installed on the inner side of the battery box (6).

3. The aircraft structure with wing folding and tail swinging functions as claimed in claim 1, characterized in that: The aircraft propulsion mechanism comprises: a propulsion cylinder (305), a sliding plate (306), a fixed plate (307) and a compression spring (308); the propulsion cylinder (305) is fixedly connected to the upper end of the rear end of the cabin (3); the sliding plate (306) is slidably connected to the inner side of the propulsion cylinder (305); the fixed plate (307) is fixedly connected to the front end surface of the sliding plate (306); the front end of the compression spring (308) is fixedly connected to the inner side of the propulsion cylinder (305), and the rear end of the compression spring (308) is fixedly connected to the front end surface of the sliding plate (306).

4. An aircraft structure with wing folding and tail swinging functions as claimed in claim 3, characterized in that: The aircraft propulsion mechanism further comprises: a limit slider (309), a limit spring (310) and a first connecting rope (311); the limit slider (309) is slidably connected to the inner side of the propulsion cylinder (305), and the limit slider (309) is plugged into the inner side of the fixing plate (307); the upper end of the limit spring (310) is fixedly connected to the lower end surface of the limit slider (309), and the lower end of the limit spring (310) is fixedly connected to the inner side of the propulsion cylinder (305); the upper end of the first connecting rope (311) is fixedly connected to the lower end surface of the limit slider (309), and the lower end of the first connecting rope (311) is fixedly connected to the outer side of the rear end control rod (401).

5. The aircraft structure with wing folding and tail swinging functions as claimed in claim 1, characterized in that: The aircraft control mechanism comprises: a folding wing (203) and an elastic member (204); two folding wings (203) are provided, and the two folding wings (203) are both hinged on the outside of the fixed wing (2); and two groups of elastic members (204) are provided, and the two ends of the two groups of elastic members (204) are respectively fixedly connected to the upper end surfaces of the fixed wing (2) and the folding wing (203).

6. An aircraft structure with wing folding and tail swinging functions as claimed in claim 5, characterized in that: The aircraft control mechanism further comprises: an articulated rod (8) and a second connecting rope (801); two articulated rods (8) are provided, and the two articulated rods (8) are both articulated on the outside of the mounting tube (201); two second connecting ropes (801) are provided, and the front ends of the two second connecting ropes (801) are respectively fixedly connected to the outsides of the two control rods (401), and the rear ends of the two second connecting ropes (801) are respectively fixedly connected to the outsides of the two articulated rods (8).

7. An aircraft structure with wing folding and tail swinging functions as claimed in claim 6, characterized in that: The aircraft control mechanism further comprises: an installation tail (9), an installation slider (901), a steering tail (902), a connecting block (903) and a connecting slide groove (904); the installation tail (9) is provided with two, and the two installation tails (9) are respectively installed on the outside of the two fixed blocks (101); the installation slider (901) is provided with two, and the two installation sliders (901) are respectively fixedly connected to the outside of the two installation tails (9), and the two installation sliders (901) are respectively slidably connected to the two installation slide grooves (102); the steering tail (902) is provided with two, and the two steering tails (902) are respectively hinged to the rear ends of the two installation tails (9); the connecting block (903) is fixedly connected to the upper end surfaces of the two steering tails (902); the connecting slide groove (904) is provided with two, and the two connecting slide grooves (904) are respectively opened on the inner sides of the two connecting blocks (903).

8. An aircraft structure with wing folding and tail swinging functions as claimed in claim 7, characterized in that: The aircraft control mechanism further comprises: a limit mounting block (10) and a mounting bolt (1001); two limit mounting blocks (10) are provided, and the two limit mounting blocks (10) are respectively slidably connected to the inner sides of the two mounting slide grooves (102); and two mounting bolts (1001) are provided, and the two mounting bolts (1001) are respectively threadedly connected to the inner sides of the two fixing blocks (101).

9. An aircraft structure with wing folding and tail swinging functions as claimed in claim 8, characterized in that: The aircraft control mechanism further comprises: an adjusting connecting rod (11); two adjusting connecting rods (11) are provided, the front ends of the two adjusting connecting rods (11) are respectively fixedly connected to the outsides of the two control rods (401), and the rear ends of the two adjusting connecting rods (11) are respectively slidably connected to the insides of the two connecting sliding grooves (904).

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