An energy-saving and wind-proof fixed-wing UAV

Abstract

The present invention discloses an energy-saving and wind-proof fixed-wing unmanned aerial vehicle, which includes a fuselage, a wind-gathering component, first to fourth positioning components, a first wing and a second wing. In the present invention, extension wing plates are arranged in the first and second wing mechanisms, folding wing plates are arranged in the extension wing plates, and the extension wing plates are triggered by the wind-gathering component, so that the wind force in the external environment during the flight of the unmanned aerial vehicle can be well monitored. At the same time, when the environmental wind force is relatively large, the automatic and rapid expansion of the extension wing plates is triggered, so that the effective area of the wing mechanism can be effectively increased. The expanded wing area can effectively improve the lifting force of the unmanned aerial vehicle, and at the same time can improve the flight stability of the unmanned aerial vehicle, thus achieving a good wind-resistant effect and avoiding the situation of the unmanned aerial vehicle getting out of control, and the application effect is good.

Description

Technical Field

[0001] The present invention relates to the technical field of fixed-wing unmanned aerial vehicles, and in particular to an energy-saving and windproof fixed-wing unmanned aerial vehicle. Background Art

[0002] As the name suggests, a drone is an autonomous aircraft that does not require human operation. It is mainly an unmanned aircraft controlled by radio remote control equipment and self-contained remote program control devices, or is operated completely or intermittently autonomously by an onboard computer.

[0003] The Chinese patent disclosed (CN110498042A), a fixed-wing aerial survey UAV, has detachable left and right wings installed on both sides of the fuselage, the flight control system includes a main control board, an azimuth acquisition sensor, an airspeed sensor, a servo, and a rudder angle; the control system includes a communication module that interacts with a ground control station, and the communication module is electrically connected to the main control board; the ground control station is responsible for controlling the entire operation process of the UAV, and the communication module is responsible for sending commands issued by the ground control station to the UAV, and transmitting the status information of the UAV back to the ground control station; the aerial survey components include a camera, a camera shock pad and a shutter control line; the power system includes an electronic speed regulator, a propeller and a motor that drives the propeller. The miniaturization of aerial survey UAVs has been achieved, and the high degree of automation of aerial survey has been achieved, making aerial survey more flexible and adaptable to various small-scale rapid measurement requirements. Today's drones are not equipped with expansion stabilization components. When the drone is flying, if there is a strong wind in the environment, it is easy to cause the drone's attitude to change, resulting in the drone's imbalance. The drone cannot fly stably or even crashes. The use effect is very poor and the safety of use is not high. In order to effectively solve the above problems, energy-saving and windproof fixed-wing drones are urgently needed. Summary of the invention

[0004] The technical problem to be solved by the present invention is to provide an energy-saving and windproof fixed-wing UAV in view of the defects involved in the background technology.

[0005] The present invention adopts the following technical solutions to solve the above technical problems:

[0006] An energy-saving and windproof fixed-wing UAV comprises a fuselage, a wind gathering component, first to fourth positioning components, a first wing and a second wing;

[0007] The first wing and the second wing have the same structure, and both include a wing body, an extended wing panel, N extended springs, a folded wing panel, M upper springs, a return spring, a positioning column, a first mounting pin and a second mounting pin, and N and M are both natural numbers greater than or equal to 1;

[0008] The extended wing plate is in the form of a rectangular parallelepiped, and a first groove for placing the folded wing plate and a first blind hole for setting the locking column are provided on the upper surface of the extended wing plate;

[0009] A second groove for placing the extended wing panel is provided on the rear side of the wing body, and a plurality of extended slide grooves parallel to the fuselage are provided on the lower end surface of the second groove, and each of the extended slide grooves is provided with an extended slider that can slide freely; a locking through hole connected to the first groove and used to cooperate with the locking column is provided on the upper surface of the wing body;

[0010] The expansion wing plate is arranged in the second groove, and is fixedly connected to the expansion slider in each expansion slide slot, and can slide freely along the expansion slide slot;

[0011] The N expansion springs are equidistantly arranged between the front end side wall of the second groove and the expansion wing plate, are parallel to the fuselage direction and are in a compressed state;

[0012] The locking column is a cylinder with a hemispherical locking bead at the upper end, and the diameter of the cross section of the column is larger than the diameter of the locking through hole; the return spring is arranged in the first blind hole, one end of which is fixedly connected to the bottom of the first blind hole, and the other end of which is fixedly connected to the lower end surface of the locking column, and is in a compressed state, so that when the expansion wing plate is completely received in the second groove, a part of the locking bead on the locking column is exposed from the locking through hole, limiting the expansion wing plate so that it cannot pop out under the elastic force of the N expansion springs;

[0013] The foldable wing plate is in the form of a rectangular parallelepiped and is arranged in the first groove, and its two sides are respectively hinged to the side walls of the second groove, so that the foldable wing plate can be rotated upward from the first groove relative to the extended wing plate to form a 90° angle with the wing plate; a plurality of mounting through holes are arranged on the foldable wing plate, and each of the mounting holes is provided with a built-in fan blade;

[0014] The M top springs are all arranged on the lower end surface of the first groove, and the lower ends are all fixedly connected to the first groove; the upper end surface of the folding wing plate abuts against the upper end side wall of the second groove, and the lower end surface presses on the M top springs, so that the M top springs are in a compressed state; the M top springs are used to bounce the folding wing plate out of the first groove when the extended wing plate pops out of the second groove, so that the folding wing plate rotates upward to form a 90° angle with the wing plate;

[0015] The first mounting pin and the second mounting pin have the same structure, both are cylindrical, and one end of each is vertically fixed to the root of the wing body and parallel to the side wall of the fuselage; the side walls of the first mounting pin and the second mounting pin are each provided with a second blind hole with the opening facing upward, and the bottom of the second blind hole is provided with an adsorption magnet;

[0016] A first mounting hole and a second mounting hole are provided on one side of the fuselage, and a third mounting hole and a fourth mounting hole are provided on the other side, wherein the first and third mounting holes are symmetrical to each other, and the second and fourth mounting holes are symmetrical to each other; first to fourth positioning holes are also provided on the upper surface of the fuselage and are in one-to-one correspondence with the first to fourth mounting holes;

[0017] The first to fourth mounting assemblies have the same structure and all include a positioning pin, a cylinder shell and a push-pull rod; the cylinder shell is a hollow cylinder with a closed upper end and an open lower end, and a first through groove for limiting the travel of the push-pull rod is provided on its side wall along its length direction; the upper end of the positioning pin extends into the cylinder shell from the lower end of the cylinder shell, and an adsorption magnet is provided at the bottom of the positioning pin; one end of the push-pull rod extends into the cylinder shell from the outside of the first through groove and is vertically fixedly connected to the positioning pin, so as to pull the positioning pin to slide up and down in the cylinder shell;

[0018] The first mounting pin and the second mounting pin of the first wing are respectively inserted into the first mounting hole and the second mounting hole, and the second blind holes of the first mounting pin and the second mounting pin of the first wing are respectively coaxial with the first mounting hole and the second mounting hole; the first mounting pin and the second mounting pin of the second wing are respectively inserted into the third mounting hole and the fourth mounting hole, and the second blind holes of the first mounting pin and the second mounting pin of the second wing are respectively coaxial with the third mounting hole and the fourth mounting hole;

[0019] The barrel shells of the first to fourth mounting components are arranged on the first to fourth positioning sockets in a one-to-one correspondence and are all fixedly connected to the fuselage, so that the positioning pins of the first to fourth mounting components are inserted from the first to fourth positioning sockets in a one-to-one correspondence and are inserted into the second blind holes of the first mounting pin of the first wing, the second mounting pin of the first wing, the first mounting pin of the second wing, and the second mounting pin of the second wing in a one-to-one correspondence, and the adsorption magnets at the bottom of the positioning pins in the first to fourth mounting components and the adsorption magnets in the second blind holes of the first mounting pin of the first wing, the second mounting pin of the first wing, the first mounting pin of the second wing, and the second mounting pin of the second wing are adsorbed in a one-to-one correspondence;

[0020] The wind gathering assembly comprises a fixed shell, a pressure bearing shaft, a pressure bearing spring, a pressure bearing block, and first and second contact pressure push rods;

[0021] The fixed shell is arranged between the first wing and the second wing, and is a hollow cuboid with openings at the lower end and the front end, and the lower end is fixedly connected to the fuselage; the side walls on both sides of the fixed shell are symmetrically provided with second and third through grooves along the length direction of the fuselage, and the rear side wall of the fixed shell is provided with a pressure-bearing through hole for the pressure-bearing shaft to pass through; the upper end surface of the fuselage is provided with a pressure-bearing slide rail in the fixed shell along the length direction of the fuselage, so that the second through groove and the third through groove are symmetrical about the pressure-bearing slide rail;

[0022] The pressure-bearing block is a rectangular parallelepiped, and a pressure-bearing slide groove is provided at the bottom thereof; the pressure-bearing slide groove cooperates with the pressure-bearing slide rail, so that the pressure-bearing block can slide freely along the pressure-bearing slide rail; the side walls on both sides of the pressure-bearing block are symmetrical about the pressure-bearing slide groove;

[0023] One end of the pressure-bearing shaft is vertically fixedly connected to the center of the rear side wall of the pressure-bearing block, and the other end passes through the pressure-bearing through hole to the outside of the fixed shell;

[0024] The pressure spring is sleeved on the pressure shaft, one end of which abuts against the pressure block, and the other end abuts against the fixed shell;

[0025] The first touch-pressure push rod and the second touch-pressure push rod are symmetrically arranged on both sides of the pressure block; one end of the first touch-pressure push rod and the second touch-pressure push rod extend into the fixed shell from the second through groove and the third through groove respectively, and are vertically fixedly connected to the side walls on both sides of the pressure block respectively; the other ends of the first touch-pressure push rod and the second touch-pressure push rod are provided with spherical touch-pressure parts, and the touch-pressure parts of the first touch-pressure push rod and the second touch-pressure push rod respectively correspond to the positioning beads at the upper ends of the positioning columns in the first wing and the second wing, so that when the speed of the UAV exceeds a preset speed threshold, the pressure block drives the positioning beads at the upper ends of the positioning columns in the first wing and the second wing to make the extended wing panels in the first wing and the second wing pop out.

[0026] As a further optimization solution of the energy-saving and windproof fixed-wing UAV of the present invention, the outer surface of the fuselage is provided with a plurality of guide grooves along its length direction.

[0027] Compared with the prior art, the present invention adopts the above technical solution and has the following technical effects:

[0028] 1. The present invention provides an expansion wing panel in the first and second wings, and a wind gathering component is provided outside. When the drone is flying normally, external airflow continuously flows into the wind gathering component, and the pressure of the airflow causes the pressure bearing block to be displaced by a certain amount. When the pressure bearing block is displaced, the first and second touch-pressure push rods are driven to be displaced synchronously. When the environmental wind force is relatively strong, the displacement of the touch-pressure push rod is increased, and the touch-pressure parts of the first and second touch-pressure push rods press the positioning beads at the upper ends of the positioning columns in the first and second wings, so that the expansion wing panels in the first and second wings are popped out. Through this structural design, the wind force in the external environment during the flight of the drone can be well monitored. At the same time, when the environmental wind force is relatively strong, the expansion wing panel can be automatically and quickly expanded, thereby effectively increasing the effective area of ​​the wing mechanism. The expanded wing area can effectively increase the lifting force of the drone, and at the same time can improve the flight stability of the drone, thereby achieving a good wind resistance effect, avoiding the situation where the drone is out of control, and having a good application effect.

[0029] 2. The invention provides an automatically opened folding wing panel in the expansion wing panel. After the stable expansion wing assembly is automatically expanded, the obstruction above the folding wing panel disappears, and the upper spring can automatically rebound the folding wing panel to automatically fold the folding wing panel. When the UAV is flying, the air resistance can further push the folding wing panel to form a right angle with the expansion wing, which can further increase the contact area between the wing and the air, and further improve the stability of the UAV. At the same time, when flying, the built-in fan blades in the folding wing panel will also automatically rotate under the action of the airflow, providing a certain driving force, effectively ensuring the energy saving of the UAV;

[0030] 3. The present invention is provided with a positioning assembly on the outside. When the wing mechanism is assembled, the wing mechanism is inserted into the mounting socket provided on the side wall of the fuselage through the mounting pin. When the second blind hole of the mounting pin is located directly below the corresponding positioning socket, the adsorption magnet in the second blind hole and the adsorption magnet at the bottom of the positioning pin are correspondingly adsorbed, thereby attracting the positioning pin downward until it is inserted into the second blind hole in the mounting pin, thereby completing the rapid and stable installation of the wing mechanism without the need for additional operations or the use of installation tools and installation parts. The installation is convenient and quick. When disassembling, the positioning pin can be pulled up by the push-pull rod, and the use effect is good. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 It is a structural schematic diagram of the present invention;

[0032] Figure 2 It is a schematic diagram of the exploded structure of the first wing in the present invention;

[0033] Figure 3 It is a schematic diagram of the explosion structure in which the extended wing plate and the folded wing plate cooperate with each other in the present invention;

[0034] Figure 4 for Figure 3 The structural diagram at B in the middle;

[0035] Figure 5 It is a schematic diagram of the explosion structure of the present invention;

[0036] Figure 6 It is a schematic diagram of the exploded structure of the first positioning assembly in the present invention;

[0037] Figure 7 It is a schematic diagram of the explosion structure of the wind gathering component in the present invention;

[0038] Figure 8 for Figure 1 Schematic diagram of the structure at A in the middle.

[0039] In the figure, 1-guide groove, 2-fuselage, 3-wind gathering component, 4-first wing, 5-first positioning component, 6-pressure slide rail, 31-fixed shell, 32-second through groove, 33-pressure shaft, 34-pressure block, 35-first contact pressure push rod, 36-pressure slide groove, 41-extension wing plate, 42-second blind hole on the first mounting pin, 43-wing body, 44-first mounting pin, 51-cylinder shell, 52-first through groove, 53-push-pull rod, 54-adsorption magnet at the bottom of the positioning pin, 55-positioning pin, 411-built-in fan blade, 412-folding wing plate, 413-extension wing plate, 414-extension spring, 415-upper spring, 416-positioning bead at the upper end of the positioning column, 417-first groove, 418-reset spring, 419-positioning through hole. DETAILED DESCRIPTION

[0040] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0041] like Figure 1 As shown, the present invention discloses an energy-saving and windproof fixed-wing UAV, comprising a fuselage, a wind gathering component, first to fourth positioning components, a first wing and a second wing;

[0042] The first wing and the second wing have the same structure, and both include a wing body, an extended wing panel, N extended springs, a folded wing panel, M upper springs, a return spring, a positioning column, a first mounting pin and a second mounting pin, and N and M are both natural numbers greater than or equal to 1;

[0043] The extended wing plate is in the form of a rectangular parallelepiped, and a first groove for placing the folded wing plate and a first blind hole for setting the locking column are provided on the upper surface of the extended wing plate;

[0044] like Figure 2 As shown, a second groove for placing the extended wing panel is provided on the rear side of the wing body, a plurality of extended slide grooves parallel to the fuselage are provided on the lower end surface of the second groove, and each of the extended slide grooves is provided with an extended slider that can slide freely; a locking through hole connected to the first groove and used to cooperate with the locking column is provided on the upper surface of the wing body;

[0045] The expansion wing plate is arranged in the second groove, and is fixedly connected to the expansion slider in each expansion slide slot, and can slide freely along the expansion slide slot;

[0046] The N expansion springs are equidistantly arranged between the front end side wall of the second groove and the expansion wing plate, are parallel to the fuselage direction and are in a compressed state;

[0047] like Figure 3 , Figure 4 As shown, the locking column is a cylinder with a hemispherical locking bead on the upper end, and the diameter of the cross section of the column is larger than the diameter of the locking through hole; the return spring is arranged in the first blind hole, one end of which is fixedly connected to the bottom of the first blind hole, and the other end is fixedly connected to the lower end surface of the locking column, and is in a compressed state, so that when the expansion wing plate is completely received in the second groove, a part of the locking bead on the locking column is exposed from the locking through hole, limiting the expansion wing plate so that it cannot pop out under the elastic force of N expansion springs;

[0048] like Figure 3 As shown, the foldable wing plate is in the form of a rectangular parallelepiped and is arranged in the first groove, and its two sides are respectively hinged to the side walls of the second groove, so that the foldable wing plate can be rotated upward from the first groove relative to the extended wing plate to form a 90° angle with the wing plate; a plurality of mounting through holes are arranged on the foldable wing plate, and each of the mounting holes is provided with a built-in fan blade;

[0049] The M top springs are all arranged on the lower end surface of the first groove, and the lower ends are all fixedly connected to the first groove; the upper end surface of the folding wing plate abuts against the upper end side wall of the second groove, and the lower end surface presses on the M top springs, so that the M top springs are in a compressed state; the M top springs are used to bounce the folding wing plate out of the first groove when the extended wing plate pops out of the second groove, so that the folding wing plate rotates upward to form a 90° angle with the wing plate;

[0050] like Figure 2 As shown, the first mounting pin and the second mounting pin have the same structure, both are cylindrical, and one end of each is vertically fixed to the root of the wing body parallel to the side wall of the fuselage; the side walls of the first mounting pin and the second mounting pin are each provided with a second blind hole with the opening facing upward, and the bottom of the second blind hole is provided with an adsorption magnet;

[0051] like Figure 5 As shown, a first mounting hole and a second mounting hole are provided on one side of the fuselage, and a third mounting hole and a fourth mounting hole are provided on the other side, wherein the first and third mounting holes are symmetrical to each other, and the second and fourth mounting holes are symmetrical to each other; first to fourth positioning holes are also provided on the upper surface of the fuselage and are in one-to-one correspondence with the first to fourth mounting holes;

[0052] like Figure 6As shown, the first to fourth mounting assemblies have the same structure, and all include a positioning pin, a cylinder shell and a push-pull rod; the cylinder shell is a hollow cylinder with a closed upper end and an open lower end, and a first through groove for limiting the stroke of the push-pull rod is provided on its side wall along its length direction; the upper end of the positioning pin extends into the cylinder shell from the lower end of the cylinder shell, and an adsorption magnet is provided at the bottom of the positioning pin; one end of the push-pull rod extends into the cylinder shell from the outside of the first through groove and is vertically fixed to the positioning pin, and is used to pull the positioning pin to slide up and down in the cylinder shell;

[0053] like Figure 5 As shown, the first mounting pin and the second mounting pin of the first wing are respectively inserted into the first mounting hole and the second mounting hole, and the second blind holes of the first mounting pin and the second mounting pin of the first wing are respectively coaxial with the first mounting hole and the second mounting hole; the first mounting pin and the second mounting pin of the second wing are respectively inserted into the third mounting hole and the fourth mounting hole, and the second blind holes of the first mounting pin and the second mounting pin of the second wing are respectively coaxial with the third mounting hole and the fourth mounting hole;

[0054] The barrel shells of the first to fourth mounting components are arranged on the first to fourth positioning sockets in a one-to-one correspondence and are all fixedly connected to the fuselage, so that the positioning pins of the first to fourth mounting components are inserted from the first to fourth positioning sockets in a one-to-one correspondence and are inserted into the second blind holes of the first mounting pin of the first wing, the second mounting pin of the first wing, the first mounting pin of the second wing, and the second mounting pin of the second wing in a one-to-one correspondence, and the adsorption magnets at the bottom of the positioning pins in the first to fourth mounting components and the adsorption magnets in the second blind holes of the first mounting pin of the first wing, the second mounting pin of the first wing, the first mounting pin of the second wing, and the second mounting pin of the second wing are adsorbed in a one-to-one correspondence;

[0055] like Figure 7 As shown, the wind gathering assembly includes a fixed shell, a pressure-bearing shaft, a pressure-bearing spring, a pressure-bearing block, and first to second contact pressure push rods;

[0056] The fixed shell is arranged between the first wing and the second wing, and is a hollow cuboid with openings at the lower end and the front end, and the lower end is fixedly connected to the fuselage; the side walls on both sides of the fixed shell are symmetrically provided with second and third through grooves along the length direction of the fuselage, and the rear side wall of the fixed shell is provided with a pressure-bearing through hole for the pressure-bearing shaft to pass through; the upper end surface of the fuselage is provided with a pressure-bearing slide rail in the fixed shell along the length direction of the fuselage, so that the second through groove and the third through groove are symmetrical about the pressure-bearing slide rail;

[0057] The pressure-bearing block is a rectangular parallelepiped, and a pressure-bearing slide groove is provided at the bottom thereof; the pressure-bearing slide groove cooperates with the pressure-bearing slide rail, so that the pressure-bearing block can slide freely along the pressure-bearing slide rail; the side walls on both sides of the pressure-bearing block are symmetrical about the pressure-bearing slide groove;

[0058] One end of the pressure-bearing shaft is vertically fixedly connected to the center of the rear side wall of the pressure-bearing block, and the other end passes through the pressure-bearing through hole to the outside of the fixed shell;

[0059] The pressure spring is sleeved on the pressure shaft, one end of which abuts against the pressure block, and the other end abuts against the fixed shell;

[0060] like Figure 8 As shown, the first touch-pressure push rod and the second touch-pressure push rod are symmetrically arranged on both sides of the pressure block; one end of the first touch-pressure push rod and the second touch-pressure push rod respectively extend into the fixed shell from the second through groove and the third through groove and are vertically fixedly connected to the side walls on both sides of the pressure block; the other ends of the first touch-pressure push rod and the second touch-pressure push rod are provided with spherical touch-pressure parts, and the touch-pressure parts of the first touch-pressure push rod and the second touch-pressure push rod respectively correspond to the positioning beads at the upper ends of the positioning columns in the first wing and the second wing, so that when the speed of the drone exceeds a preset speed threshold, the pressure block drives the positioning beads at the upper ends of the positioning columns in the first wing and the second wing to make the extended wing panels in the first wing and the second wing pop out.

[0061] The outer surface of the fuselage is provided with a plurality of guide grooves along its length direction.

[0062] When assembling the wing mechanism, the wing mechanism is inserted into the installation socket set on the side wall of the fuselage through the installation pin. When the second blind hole of the installation pin is located directly below the corresponding positioning socket, the adsorption magnet in the second blind hole and the adsorption magnet at the bottom of the positioning pin are correspondingly adsorbed, thereby attracting the positioning pin downward until it is stuck in the second blind hole in the installation pin, thereby completing the rapid and stable installation of the wing mechanism. No additional operation is required, and no installation tools and installation parts are required. The installation is convenient and quick. When disassembling, the positioning pin can be pulled up by the push-pull rod, and the use effect is good.

[0063] When the UAV is flying normally, external airflow continuously flows into the wind gathering component, and the pressure of the airflow causes the pressure-bearing block to displace a certain amount. When the pressure-bearing block is displaced, it drives the first and second touch-pressure push rods to displace synchronously. When the environmental wind force is strong, the displacement of the touch-pressure push rods increases, and the touch-pressure parts of the first and second touch-pressure push rods press the positioning beads at the upper ends of the positioning columns in the first and second wings, so that the extended wing panels in the first and second wings pop out. Through this structural design, the wind force in the external environment when the UAV is flying can be well monitored. At the same time, when the environmental wind force is strong, the extended wing panel can be automatically and quickly expanded, thereby effectively increasing the effective area of ​​the wing mechanism. The expanded wing area can effectively increase the lift of the UAV and improve the flight stability of the UAV, thereby achieving a good wind resistance effect and avoiding the situation where the UAV loses control, with good application effect.

[0064] After the stable expansion wing assembly automatically expands, the obstruction above the folding wing panel disappears, and the upper spring can automatically rebound against the folding wing panel to make the folding wing panel automatically fold. When the UAV is flying, the air resistance can further push the folded wing panel to form a right angle with the expanded wing, which can further increase the contact area between the wing and the air and further improve the stability of the UAV. At the same time, during flight, the built-in fan blades in the folding wing panel will automatically rotate under the action of the airflow, providing a certain driving force, effectively ensuring the energy saving of the UAV.

[0065] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. An energy-saving and windproof fixed-wing UAV, It is characterized in that It comprises a fuselage, a wind gathering component, first to fourth positioning components, a first wing and a second wing; The first wing and the second wing have the same structure, and both include a wing body, an extended wing panel, N extended springs, a folded wing panel, M upper springs, a return spring, a positioning column, a first mounting pin and a second mounting pin, and N and M are both natural numbers greater than or equal to 1; The extended wing plate is in the form of a rectangular parallelepiped, and a first groove for placing the folded wing plate and a first blind hole for setting the locking column are provided on the upper surface of the extended wing plate; A second groove for placing the extended wing panel is provided on the rear side of the wing body, and a plurality of extended slide grooves parallel to the fuselage are provided on the lower end surface of the second groove, and each of the extended slide grooves is provided with an extended slider that can slide freely; a locking through hole connected to the first groove and used to cooperate with the locking column is provided on the upper surface of the wing body; The expansion wing plate is arranged in the second groove, and is fixedly connected to the expansion slider in each expansion slide slot, and can slide freely along the expansion slide slot; The N expansion springs are equidistantly arranged between the front end side wall of the second groove and the expansion wing plate, are parallel to the fuselage direction and are in a compressed state; The locking column is a cylinder with a hemispherical locking bead at the upper end, and the diameter of the cross section of the column is larger than the diameter of the locking through hole; the return spring is arranged in the first blind hole, one end of which is fixedly connected to the bottom of the first blind hole, and the other end of which is fixedly connected to the lower end surface of the locking column, and is in a compressed state, so that when the expansion wing plate is completely received in the second groove, a part of the locking bead on the locking column is exposed from the locking through hole, limiting the expansion wing plate so that it cannot pop out under the elastic force of the N expansion springs; The foldable wing plate is in the form of a rectangular parallelepiped and is arranged in the first groove, and its two sides are respectively hinged to the side walls of the second groove, so that the foldable wing plate can be rotated upward from the first groove relative to the extended wing plate to form a 90° angle with the wing plate; a plurality of mounting through holes are arranged on the foldable wing plate, and each of the mounting holes is provided with a built-in fan blade; The M top springs are all arranged on the lower end surface of the first groove, and the lower ends are all fixedly connected to the first groove; the upper end surface of the folding wing plate abuts against the upper end side wall of the second groove, and the lower end surface presses on the M top springs, so that the M top springs are in a compressed state; the M top springs are used to bounce the folding wing plate out of the first groove when the extended wing plate pops out of the second groove, so that the folding wing plate rotates upward to form a 90° angle with the wing plate; The first mounting pin and the second mounting pin have the same structure, both are cylindrical, and one end of each is vertically fixed to the root of the wing body and parallel to the side wall of the fuselage; the side walls of the first mounting pin and the second mounting pin are each provided with a second blind hole with the opening facing upward, and the bottom of the second blind hole is provided with an adsorption magnet; A first mounting hole and a second mounting hole are provided on one side of the fuselage, and a third mounting hole and a fourth mounting hole are provided on the other side, wherein the first and third mounting holes are symmetrical to each other, and the second and fourth mounting holes are symmetrical to each other; first to fourth positioning holes are also provided on the upper surface of the fuselage and are in one-to-one correspondence with the first to fourth mounting holes; The first to fourth mounting assemblies have the same structure and all include a positioning pin, a cylinder shell and a push-pull rod; the cylinder shell is a hollow cylinder with a closed upper end and an open lower end, and a first through groove for limiting the travel of the push-pull rod is provided on its side wall along its length direction; the upper end of the positioning pin extends into the cylinder shell from the lower end of the cylinder shell, and an adsorption magnet is provided at the bottom of the positioning pin; one end of the push-pull rod extends into the cylinder shell from the outside of the first through groove and is vertically fixedly connected to the positioning pin, so as to pull the positioning pin to slide up and down in the cylinder shell; The first mounting pin and the second mounting pin of the first wing are respectively inserted into the first mounting hole and the second mounting hole, and the second blind holes of the first mounting pin and the second mounting pin of the first wing are respectively coaxial with the first mounting hole and the second mounting hole; the first mounting pin and the second mounting pin of the second wing are respectively inserted into the third mounting hole and the fourth mounting hole, and the second blind holes of the first mounting pin and the second mounting pin of the second wing are respectively coaxial with the third mounting hole and the fourth mounting hole; The barrel shells of the first to fourth mounting components are arranged on the first to fourth positioning sockets in a one-to-one correspondence and are all fixedly connected to the fuselage, so that the positioning pins of the first to fourth mounting components are inserted from the first to fourth positioning sockets in a one-to-one correspondence and are inserted into the second blind holes of the first mounting pin of the first wing, the second mounting pin of the first wing, the first mounting pin of the second wing, and the second mounting pin of the second wing in a one-to-one correspondence, and the adsorption magnets at the bottom of the positioning pins in the first to fourth mounting components and the adsorption magnets in the second blind holes of the first mounting pin of the first wing, the second mounting pin of the first wing, the first mounting pin of the second wing, and the second mounting pin of the second wing are adsorbed in a one-to-one correspondence; The wind gathering assembly comprises a fixed shell, a pressure bearing shaft, a pressure bearing spring, a pressure bearing block, and first and second contact pressure push rods; The fixed shell is arranged between the first wing and the second wing, and is a hollow cuboid with openings at the lower end and the front end, and the lower end is fixedly connected to the fuselage; the side walls on both sides of the fixed shell are symmetrically provided with second and third through grooves along the length direction of the fuselage, and the rear side wall of the fixed shell is provided with a pressure-bearing through hole for the pressure-bearing shaft to pass through; the upper end surface of the fuselage is provided with a pressure-bearing slide rail in the fixed shell along the length direction of the fuselage, so that the second through groove and the third through groove are symmetrical about the pressure-bearing slide rail; The pressure-bearing block is a rectangular parallelepiped, and a pressure-bearing slide groove is provided at the bottom thereof; the pressure-bearing slide groove cooperates with the pressure-bearing slide rail, so that the pressure-bearing block can slide freely along the pressure-bearing slide rail; the side walls on both sides of the pressure-bearing block are symmetrical about the pressure-bearing slide groove; One end of the pressure-bearing shaft is vertically fixedly connected to the center of the rear side wall of the pressure-bearing block, and the other end passes through the pressure-bearing through hole to the outside of the fixed shell; The pressure spring is sleeved on the pressure shaft, one end of which abuts against the pressure block, and the other end abuts against the fixed shell; The first touch-pressure push rod and the second touch-pressure push rod are symmetrically arranged on both sides of the pressure block; one end of the first touch-pressure push rod and the second touch-pressure push rod extend into the fixed shell from the second through groove and the third through groove respectively, and are vertically fixedly connected to the side walls on both sides of the pressure block respectively; the other ends of the first touch-pressure push rod and the second touch-pressure push rod are provided with spherical touch-pressure parts, and the touch-pressure parts of the first touch-pressure push rod and the second touch-pressure push rod respectively correspond to the positioning beads at the upper ends of the positioning columns in the first wing and the second wing, so that when the speed of the UAV exceeds a preset speed threshold, the pressure block drives the positioning beads at the upper ends of the positioning columns in the first wing and the second wing to make the extended wing panels in the first wing and the second wing pop out.

2. The energy-saving and windproof fixed-wing UAV according to claim 1, It is characterized in that The outer surface of the fuselage is provided with a plurality of guide grooves along its length direction.

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