Bionic folding wing unmanned glider

Abstract

The present application belongs to the technical field of unmanned aerial vehicle, and particularly relates to a bionic folding wing unmanned glider. The present application comprises a nose, a fuselage and a tail connected in sequence, two folding wings and a plurality of unfolding ducts arranged in the folding wings, an explosive power device and two groups of filler storage assemblies. The bionic tail rotor is driven to rotate by wind force when the aerial vehicle descends, the collision explosive stored in the trigger screw is triggered to enter the explosion chamber to explode, the explosion thrust of the collision explosive pushes the propelling piston arranged in the explosion chamber to the side of the unfolding duct, so that the filler entering the explosion chamber is extruded into the plurality of unfolding ducts, i.e. the folding wings are unfolded. The filler hardens in a short time, so that the unfolded state of the folding wings is maintained, and internal fuel combustion is not needed to generate high heat to provide driving force, solving the problem of heavy load and high heat easily tracked by fuel combustion driving in the prior art.

Description

Technical Field

[0001] This invention belongs to the field of unmanned aerial vehicle technology, specifically relating to a biomimetic folding-wing unmanned glider. Background Technology

[0002] Unmanned aerial vehicles (UAVs) complete pre-set tasks under the command of humans or computers through intelligent control technology and network information systems. In recent years, UAVs have been widely used in mapping and military fields. Especially in the military field, formations of hundreds or even larger UAVs can expand the reconnaissance and search area, and can also achieve penetration or large-scale fire coverage, rendering existing defenses ineffective or paralyzed.

[0003] Currently, most aircraft used in the military and cartographic fields rely on jet rocket engines for propulsion. These engines generate high heat through internal combustion to provide active propulsion. This method of propulsion presents the following problems:

[0004] (1) The internal combustion generates high heat, making it easy to track and destroy;

[0005] (2) It is necessary to place fuel inside the aircraft, which increases the aircraft's weight and contradicts the requirement that the aircraft be lightweight and flexible;

[0006] (3) High energy consumption and high cost.

[0007] Based on the above problems, there is an urgent need for an unmanned glider that does not require internal combustion or other means of propulsion, and is small in size, low in cost, reliable in deployment, and has stealth capabilities. Summary of the Invention

[0008] The purpose of this invention is to overcome the shortcomings of existing unmanned aerial vehicles (UAVs) such as high heat generation, easy tracking, large size, and high cost, and to provide a biomimetic folding-wing unmanned glider that does not require internal combustion, automatically deploys its folding wings, and has a large gliding distance.

[0009] The technical solution adopted by this invention to solve its technical problem is: a biomimetic folding-wing unmanned gliding aircraft, comprising:

[0010] The nose, fuselage, and tail are connected in sequence;

[0011] Two folding wings and multiple deployment ducts disposed within the folding wings; the folding wings are embedded and installed on the outside of the fuselage, and the deployment ducts communicate with the fuselage cavity;

[0012] An explosive power unit, installed inside the fuselage, provides power for the deployment of the folding wings. The explosive power unit includes an actuator cylinder, explosive blocks symmetrically arranged on both sides of the actuator cylinder, a threaded hole in the middle of the actuator cylinder, a trigger screw that engages with the threaded hole, and a bionic tail rotor installed at the tail end of the trigger screw. Several explosive chambers are provided on each explosive block, and a propulsion piston is installed within each explosive chamber. Multiple transverse through holes are provided on the trigger screw for storing impact explosives. Each transverse through hole corresponds to one of the explosive chambers and is connected to them via flow channels; each explosive chamber corresponds to one of the deployment pipes and is connected to them via liquid channels.

[0013] Two sets of filler storage assemblies are installed at the tail end of the explosive block to provide filler to the deployment pipe; wherein, the filler storage assembly is connected to the liquid circuit of the explosive chamber, and when the impact explosive explodes by colliding with the propulsion piston, the propulsion piston is pushed to squeeze the filler flowing into the explosive chamber into the deployment pipe.

[0014] Furthermore, the side of the propulsion piston near the trigger screw is provided with several impact protrusions, and / or a carbon dioxide tank is provided in the explosion chamber on the side of the propulsion piston near the trigger screw.

[0015] Furthermore, the filler storage assembly includes a storage tank, a partition plate installed inside the storage tank, a liquid outlet opened on the mounting surface of the storage tank and the explosive block, a liquid outlet baffle plate disposed between the storage tank and the explosive block, a stirring assembly installed inside the storage tank for mixing and stirring the filler flowing into the liquid outlet, and a liquid outlet control assembly for controlling the liquid outlet baffle plate to block the liquid outlet.

[0016] The partition plate divides the liquid storage tank and the liquid outlet into two parts. The liquid outlet is connected to the corresponding multiple explosion chambers through a first flow channel, which is located on the outside of the propulsion piston.

[0017] Furthermore, the liquid discharge control component includes:

[0018] Two limiting protrusions are fixedly installed at the tail of the explosion chamber, and the liquid outlet baffle slides within the two limiting protrusions.

[0019] The liquid discharge control gear is sleeved on the trigger screw and rotates with the trigger screw;

[0020] A liquid discharge control rack is disposed at one end of the liquid discharge baffle plate near the actuating cylinder and is connected in conjunction with the liquid discharge control gear.

[0021] Furthermore, the filler includes epoxy resin and a curing agent, which are respectively disposed in the two storage chambers of the storage tank;

[0022] The stirring assembly includes a stirring motor installed inside the storage tank and a stirring paddle coaxially arranged with the output shaft of the stirring motor; a mounting plate is provided on the partition plate, the stirring motor is installed on the lower end face of the mounting plate, and the stirring paddle extends into the inner cavity of the liquid outlet;

[0023] The inner wall of the unfolding pipe is provided with heating wires for accelerating the curing of the mixed filler.

[0024] Furthermore, the impact explosive includes at least one of silver fulminate and mercuric fulminate.

[0025] Furthermore, the nose cone is detachably connected to the fuselage, and the nose cone contains an ammunition compartment for storing ammunition.

[0026] Furthermore, the inner wall of the explosion chamber is provided with a buffer layer, which is made of one of the following materials: cross-linked polyethylene, epoxy resin, and fluffy cotton.

[0027] Furthermore, the front end of the machine head is also provided with a speed control component and / or an infrared mapping component.

[0028] Furthermore, the outer surfaces of the head, body, and tail are coated with a thermal insulation stealth coating, which is made of one of the following: a conductive polymer, a cellulose aerogel coated fabric, or a doped semiconductor material.

[0029] The beneficial effects of the biomimetic folding-wing unmanned glider of the present invention are:

[0030] This invention utilizes the wind power generated during the descent of an aircraft to drive the rotation of a biomimetic tail rotor. A trigger screw releases a stored explosive charge into an explosive chamber, where it detonates. The explosive thrust pushes a piston within the chamber towards the deployment channels, forcing the filler material into multiple deployment channels, thus deploying the folding wing. The filler material hardens quickly, maintaining the folded wing in its deployed state. This invention eliminates the need for internal fuel combustion to generate high heat for propulsion during wing deployment, solving the problems of heavy payload and easy tracking associated with fuel combustion-driven systems in existing technologies. Furthermore, the ingenious use of explosive thrust from the colliding charge significantly reduces power costs.

[0031] Meanwhile, the invention designs the nose and fuselage as detachable structures, with an ammunition compartment inside the nose for loading ammunition, eliminating the need for an external ammunition compartment, reducing wind resistance during flight, and making the aircraft smaller in size and able to fly over longer distances, greatly increasing the application scenarios of the aircraft. Attached Figure Description

[0032] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0033] Figure 1 This is a perspective view of the aircraft in Embodiment 1 of the present invention.

[0034] Figure 2 This is a cross-sectional view of the internal structure of the aircraft in Embodiment 1 of the present invention.

[0035] Figure 3 yes Figure 2 Enlarged view of point A in the middle.

[0036] Figure 4 yes Figure 2 Enlarged view of point B in the middle.

[0037] Figure 5 This is a side view of the aircraft in its initial state before the folding wings are deployed, according to Embodiment 1 of the present invention.

[0038] Figure 6 This is a partial structural schematic diagram of the aircraft in Embodiment 1 of the present invention.

[0039] Figure 7 This is a detailed diagram of the liquid discharge control component in Embodiment 1 of the present invention.

[0040] Figure 8 This is a cross-sectional view of the internal structure of the aircraft in Embodiment 2 of the present invention.

[0041] Figure 9 This is a cross-sectional view of the internal structure of the aircraft in Embodiment 3 of the present invention.

[0042] In the diagram: 1 / 1-3, Nose; 2 / 2-2 / 2-3, Fuselage; 3, Tail; 4 / 4-2, Folding Wing; 5 / 5-2, Deployment Pipe; 6, Explosive Power Unit; 61, Actuator Cylinder; 62, Explosive Block; 63 / 63-2, Trigger Screw; 64 / 64-2, Bionic Tail Rotor; 65 / 65-2, Explosive Chamber; 66 / 66-2, Propulsion Piston; 67, Lateral Through Hole; 68 / 68-2, Impact Explosive; 7, Filler Storage Assembly; 71, Liquid Storage Tank; 73, Liquid Outlet Baffle; 74, Liquid Outlet Control Assembly; 741, Limiting Protrusion; 742, Liquid Outlet Control Gear; 743, Liquid Outlet Control Rack; 75, Stirring Assembly; 751, Stirring Motor; 752, Stirring Paddle; 8, Speed ​​Control Assembly; 9, Infrared Mapping Assembly; 10, Carbon Dioxide Tank; 20, Ammunition Chamber. 30. Heating wire; 40. Power supply. Detailed Implementation

[0043] The present invention will now be described in further detail with reference to the accompanying drawings. These drawings are simplified schematic diagrams, illustrating only the basic structure of the invention, and therefore only show the components relevant to the invention.

[0044] Example 1

[0045] like Figures 1-7 The embodiment of the biomimetic folding-wing unmanned glider of the present invention shown includes: a nose 1, a fuselage 2, a tail 3 connected in sequence; two folding wings 4; multiple deployment pipes 5 disposed within the folding wings 4; an explosive propulsion device 6; and two sets of filler storage assemblies 7. The folding wings 4 are embedded and installed on the outside of the fuselage 2, and the deployment pipes 5 communicate with the cavity of the fuselage 2. The explosive power unit 6 is installed inside the fuselage 2 and is used to provide power for the deployment of the folding wing 4. The explosive power unit 6 includes an actuator 61, explosive blocks 62 symmetrically arranged on both sides of the actuator 61, a threaded hole in the middle of the actuator 61, a trigger screw 63 that cooperates with the threaded hole, and a bionic tail rotor 64 installed at the tail end of the trigger screw 63. Several explosive chambers 65 are provided on the explosive blocks 62. A propulsion piston 66 is provided in the explosive chamber 65. Multiple transverse through holes 67 for storing impact explosives 68 are provided on the trigger screw 63. The transverse through holes 67 correspond one-to-one with the explosive chambers 65 and are connected by flow channels. The explosive chambers 65 correspond one-to-one with the deployment pipes 5 and are connected by liquid channels. Two sets of filler storage components 7 are installed at the tail end of the explosive block 62 to provide filler to the deployment pipe 5. It should be noted that in this embodiment, the filler storage components 7 are connected to the liquid circuit of the explosive chamber 65. When the colliding explosive 68 collides and explodes with the propulsion piston 66, the propulsion piston 66 is pushed to squeeze the filler flowing into the explosive chamber 65 into the deployment pipe 5.

[0046] In this embodiment, the aircraft utilizes the wind power during descent to rotate the bionic tail rotor 64. A trigger screw 63 causes the explosive charge 68 stored within it to detonate inside the explosive chamber 65. The explosive thrust of the explosive charge 68 pushes the propulsion piston 66 within the explosive chamber 65 towards the deployment pipes 5, thereby forcing the filler material into the multiple deployment pipes 5, thus deploying the folding wing 4. The filler material hardens quickly, maintaining the deployed state of the folding wing 4. This invention eliminates the need for internal fuel combustion to generate high heat for propulsion during folding wing 4 deployment, solving the problems of heavy payload and easy tracking associated with fuel combustion-driven systems in existing technologies. Furthermore, the clever use of the explosive thrust of the explosive charge 68 as the power source for folding wing 4 deployment in this embodiment significantly reduces power costs.

[0047] In this first embodiment, to reduce the slight heat generated by the collision explosion of the explosive device 68 and make the aircraft stealth, a thermal insulation stealth layer is coated on the outer surfaces of the nose 1, fuselage 2, and tail 3. The thermal insulation stealth layer is made of one of the following materials: conductive polymer, cellulose aerogel coated fabric, or doped semiconductor. In this first embodiment, a trigger screw 63 is used to trigger the collision of the explosive device 68 to generate explosive thrust. The addition of the thermal insulation stealth layer completely solves the problem of the aircraft being easily tracked and detected.

[0048] To ensure the explosive thrust of the impact explosive 68, in this embodiment, several impact protrusions are provided on the side of the propulsion piston 66 near the trigger screw 63, so that the impact explosive 68 can fully collide with the propulsion piston 66. Furthermore, the inner wall of the explosive chamber 65 in this embodiment is provided with a buffer layer to ensure that the impact explosive 68 does not directly explode when it comes into contact with the inner wall of the explosive chamber 65, but only explodes when the impact explosive 68 comes into contact with the propulsion piston 66. This ensures the pushing effect of the explosive thrust on the propulsion piston 66. In this embodiment, the buffer layer is made of one of cross-linked polyethylene, epoxy resin, or fluffy cotton material, and is adhesively bonded to the inner wall of the explosive chamber 65.

[0049] It should be further noted that the impact explosive 68 includes at least one of silver fulminate and mercuric fulminate, and in this embodiment, the impact explosive 68 is a silver fulminate rolling body. It should be understood that other explosives with impact explosive function that are conceivable to those skilled in the art but not mentioned in this text should also be covered within the scope of protection of this invention.

[0050] like Figures 4 to 6As shown, the filler storage assembly 7 in this embodiment includes a liquid storage tank 71, a partition plate installed inside the liquid storage tank 71, a liquid outlet opened on the mounting surfaces of the liquid storage tank 71 and the explosive block 62, a liquid outlet baffle plate 73 disposed between the liquid storage tank 71 and the explosive block 62, a stirring assembly 75 installed inside the liquid storage tank 71 for mixing and stirring the filler flowing into the liquid outlet, and a liquid outlet control assembly 74 for controlling the liquid outlet baffle plate 73 to block the liquid outlet. The partition plate divides the liquid storage tank 71 into two liquid storage chambers, and the partition plate divides the liquid outlet into two parts, which are respectively connected to the two liquid storage chambers. The liquid outlet is connected to the corresponding multiple explosive chambers 65 through a first flow channel, which is located outside the propulsion piston 66. In this first embodiment, four protrusions are provided below the liquid storage tank 71. The four protrusions are used to separate the liquid storage tank 71 and the explosive block 62, leaving space for the liquid outlet baffle plate 73.

[0051] Of course, the specific structure of the filler storage component 7 described above is a preferred embodiment, and the structure of the filler storage component 7 is not absolutely limited. As another embodiment, the filler storage component 7 may also include two independent liquid storage tanks 71, each of which is provided with a liquid outlet, and the liquid outlets are connected to the corresponding flow channels of the explosion chamber 65. In this embodiment, the filler includes epoxy resin and a curing agent. The epoxy resin and the curing agent are respectively disposed in the two liquid storage chambers of the liquid storage tank 71. After the epoxy resin and the curing agent are fully mixed in the flow channels and the explosion chamber 65, they are squeezed into the opening pipe 5 and then cured.

[0052] To achieve thorough mixing of epoxy resin and curing agent, a stirring assembly is installed inside the storage tank. The stirring assembly 75 includes a stirring motor 751 installed inside the storage tank 71 and a stirring paddle 752 coaxially arranged with the output shaft of the stirring motor 751. A mounting plate is provided on the partition plate, the stirring motor 751 is mounted on the lower end face of the mounting plate, and the stirring paddle 752 extends into the inner cavity of the outlet.

[0053] To ensure the instantaneous curing of the mixed filler entering the unfolding pipe 5 and maintain the unfolded state of the folding wings 4, a heating wire 30 is attached to the inner wall of the unfolding pipe 5. The heating wire 30 heats the filler entering the unfolding pipe 5, shortening the curing time and ensuring the complete unfolding of the folding wings 4. It should be further noted that in this embodiment, the power supply 40, which provides power to the heating wire 30 and the stirring motor 451, is installed inside the head unit 1. The head unit 1 is designed with a hollow structure to facilitate the installation of the power supply 40.

[0054] See Figure 6In this embodiment, the liquid discharge control component 74 includes two limiting protrusions 741, a liquid discharge control gear 742, and a liquid discharge control rack 743. Specifically, during installation, the two limiting protrusions 741 are fixedly installed at the tail of the explosion chamber 65. The liquid discharge baffle 73 slides within the two limiting protrusions 741 to control the flow of liquid between the liquid outlet and the first flow channel. The liquid discharge control gear 742 is sleeved on the trigger screw 63 and rotates with the trigger screw 63. The liquid discharge control rack 743 is located at the end of the liquid discharge baffle 73 near the actuating cylinder 61 and is connected to the liquid discharge control gear 742.

[0055] In this embodiment, the trigger screw 63 is provided with three transverse through holes 67, and each of the two corresponding explosive blocks 62 is provided with three explosive chambers 65. The three explosive chambers 65 on one explosive block 62 are all connected through a flow channel. The corresponding folding wing 4 is provided with three deployment pipes 5 in parallel. When the aircraft is in its original state, the folding wing 4 is attached to the fuselage 2. When the trigger screw 63 is driven by the bionic tail rotor 64, it rotates counterclockwise, causing the trigger screw 63 to rotate and move from the central cylinder. When the trigger screw 63 moves to the point where the three transverse through holes 67 are all connected to the corresponding explosive chambers 65, the silver fulminate rolling body in the transverse through holes 67 enters the corresponding explosive chamber 65 under the action of rotational force to carry out a collision and explosion reaction.

[0056] Specifically, during the installation of the aircraft, the silver fulminate rolling elements are stored in the three transverse through holes 67 of the trigger screw 63. The tail end of the trigger screw 63 protrudes from the tail 3 and is fixedly connected to the bionic tail rotor 64 with screws, causing the bionic tail rotor 64 to move counterclockwise under the action of upward wind force. A liquid discharge control gear 742 is installed in the middle of the trigger screw 63, and a liquid discharge control rack 743 that meshes with the liquid discharge control gear 742 is set on the explosive block 62. At the same time, epoxy resin and curing agent are injected into the two liquid storage chambers of the liquid storage tank 71, respectively. A propulsion piston 66 is installed in the explosive chamber 65. The operation process of the aircraft in this embodiment is as follows:

[0057] In its initial state, the drone's two folding wings 4 are attached to the fuselage 2, as shown. Figure 5 As shown, before the folding wings 4 are deployed, the two folding wings 4 are attached to the fuselage 2 facing each other. When the aircraft descends, the folding wings 4 detach from the fuselage 2. The wind force during descent drives the bionic tail rotor 64 to rotate. The collision explosive stored in the trigger screw 63 is detonated in the explosion chamber 65 through the trigger screw 63. The explosive thrust of the collision explosive pushes the propulsion piston 66 set in the explosion chamber 65 toward the deployment pipe 5, thereby squeezing the filler that has entered the explosion chamber 65 into multiple deployment pipes 5, thus realizing the fixed deployment of the folding wings 4.

[0058] Specifically, during the free fall of the drone, the bionic tail rotor 64 begins to rotate counterclockwise under the influence of an upward wind, further driving the trigger screw 63 connected to the fuselage 2 to rotate. The liquid discharge control gear 742 on the trigger screw 63 meshes with the liquid discharge control rack 743. The counterclockwise rotation of the liquid discharge control gear 742 causes the two liquid discharge control racks 743 to move towards the center, opening the two storage tanks 71. This allows the epoxy resin storage tank 71 and the curing agent storage tank 71 inside the storage tanks 71 to be opened respectively, and under their own gravity, they flow downwards simultaneously, flowing into the flow channel connected to the folding wing 4 in the explosion chamber 65 and into the explosion chamber 65 itself. The three portions of silver fulminate stored in the trigger screw 63, as the bionic tail rotor 64 rotates counterclockwise and gradually detaches from the main body of the fuselage 2, and as the epoxy resin and curing agent in the storage tanks 71 flow downwards into the three deployment pipes 5 inside the folding wing 4, the silver fulminate interacts with the trigger screw 63. 3. They rotate together and move upward in a straight line. When they reach the corresponding explosive chamber 65, the silver fulminate is thrown into the corresponding explosive chamber 65 by inertia. The inner wall of the explosive chamber 65 is provided with a buffer layer. The surface of the corresponding propulsion piston 66 that contacts the fulminate 7 is provided with several protrusions. When the silver fulminate just connects with the storage chamber, because of the buffer layer, the silver fulminate does not explode when it comes into contact with the inner wall of the explosive chamber 65. When the silver fulminate comes into contact with the propulsion piston 66, it explodes in the explosive chamber 65. The pressure generated by the explosion pushes the propulsion piston 66 to move towards the deployment pipe 5 of the folding wing 4, accelerating the propulsion of epoxy resin and curing agent into the deployment pipe 5. The epoxy resin and curing agent quickly fill the deployment pipe 5, so that the folding wing 4 changes from being attached to the main body of the fuselage 2 to having a skeleton and being fully deployed as a flight wing. The bionic tail rotor 64 at the tail detaches from the fuselage 2 by rotation. Under the action of the deployed folding wing 4, the aircraft changes from free fall to gliding motion.

[0059] In this first embodiment, an infrared mapping component 9 can be provided at the front end of the head 1. The infrared mapping component 9 includes an infrared sensor. The infrared sensor transmitter emits infrared rays. When the infrared rays enter the ground surface, they will be absorbed, reflected or transmitted by different terrains or objects. Different surfaces have different reflectivities and absorptivity. The infrared sensor receiver receives the infrared rays reflected by the object surface and converts them into electrical signals. By processing and analyzing the received electrical signals, the terrain mapping is realized.

[0060] Example 2

[0061] The difference between this embodiment and embodiment one is that a carbon dioxide canister 10 is installed in the explosion chamber 65-2 near the trigger screw 63-2. When the impact explosive 68-2 comes into contact with the carbon dioxide canister 10, sufficient thrust is generated to push the propulsion piston 66-2 to move towards the folding wing 4-2 within the explosion chamber 65-2. This allows the filler material entering the explosion chamber 65-2 to fully fill the multiple deployment pipes 5-2 within the folding wing 4-2, causing the folding wing 4-2 to fully deploy. See details below. Figure 6 .

[0062] When the trigger screw 63-2 is in its initial state, as follows: Figure 8 As shown, when the epoxy resin and curing agent flow downwards, the silver fulminate is not connected to the explosive chamber 65-2. The initial state of the trigger screw 63-2 is shown in the figure. When the silver fulminate rolling body is connected to the explosive chamber 65-2, the epoxy resin and curing agent have flowed into the connection between the deployment pipe 5-2 and the fuselage 2-2. The silver fulminate rolling body hits the carbon dioxide tank 10 in the explosive chamber 65-2. The carbon dioxide tank 10 generates huge pressure to push the propulsion piston 66-2. Under the action of the propulsion piston 66-2, the epoxy resin and curing agent accelerate into the deployment pipe 5-2. The epoxy resin and curing agent mix and harden in a short time. The hardened epoxy resin and curing agent mixture fixes the folding wing 4-2 in place and deploys. The bionic tail rotor 64-2 continues to rotate and detaches from the main body of the fuselage 2-2. The aircraft changes from free fall to gliding motion. It should be understood that in this embodiment, the explosion chamber 65-2 on the side of the thrust piston 66-2 near the trigger screw 63-2 can be equipped with only a carbon dioxide tank 10, or it can be equipped with both a carbon dioxide tank 10 and several collision protrusions to ensure that the explosive thrust is large enough.

[0063] Example 3

[0064] like Figure 9 As shown, the difference between this third embodiment and the first or second embodiment is that a speed control component 8 is provided at the front end of the head 1-3, and the head 1-3 is detachably connected to the body 2-3. An ammunition compartment 20 for storing ammunition is provided inside the head 1-3.

[0065] In one implementation, the speed control component 8 of this embodiment includes a speed controller used to detect the descent and gliding speed of the aircraft. An ammunition magazine 20 is located within the nose section 1-3. When ammunition is loaded into the magazine 20, it can strike surface ships or attack ground targets. Furthermore, it can deploy an appropriate number of ordnance-laden gliders depending on the size of the area. In this embodiment, the nose section 1-3 and fuselage 2-3 are designed as detachable structures. The ammunition magazine 20 for loading ammunition is located inside the nose section 1-3, eliminating the need for an external ammunition magazine. This reduces wind resistance during flight, resulting in a smaller size and longer flight range, significantly increasing the aircraft's application scenarios.

[0066] It should be understood that the specific embodiments described above are for illustrative purposes only and are not intended to limit the scope of the invention. Obvious variations or modifications derived from the spirit of the invention are still within the protection scope of the invention.

Claims

1. A biomimetic folding-wing unmanned glider, characterized in that, include: The nose (1), fuselage (2), and tail (3) are connected in sequence; Two folding wings (4) and multiple deployment pipes (5) disposed within the folding wings (4); the folding wings (4) are embedded and installed on the outside of the fuselage (2), and the deployment pipes (5) are connected to the cavity of the fuselage (2); An explosive power device (6) is installed on the inner side of the fuselage (2) to provide power for the deployment of the folding wing (4); the explosive power device (6) includes an actuating cylinder (61), explosive blocks (62) symmetrically arranged on both sides of the actuating cylinder (61), a threaded hole in the middle of the actuating cylinder (61), a trigger screw (63) that cooperates with the threaded hole, and a bionic tail rotor (64) installed at the tail end of the trigger screw (63); the explosive blocks (62) are provided with a plurality of explosive chambers (65), and a propulsion piston (66) is provided in the explosive chambers (65); the trigger screw (63) is provided with a plurality of transverse through holes (67) for storing impact explosives (68); the transverse through holes (67) correspond one-to-one with the explosive chambers (65) and are connected by flow channels, and the explosive chambers (65) correspond one-to-one with the deployment pipe (5) and are connected by liquid channels; Two sets of filler storage assemblies (7) are installed at the tail end of the explosive block (62) to provide filler to the deployment pipe (5); wherein, the filler storage assembly (7) is connected to the liquid circuit of the explosive chamber (65), and when the impact explosive (68) collides and explodes with the propulsion piston (66), the propulsion piston (66) is pushed to squeeze the filler flowing into the explosive chamber (65) into the deployment pipe (5).

2. The biomimetic folding-wing unmanned glider according to claim 1, characterized in that: The propulsion piston (66) is provided with a plurality of collision protrusions on the side near the trigger screw (63), and / or a carbon dioxide tank (10) is provided in the explosion chamber (65) on the side of the propulsion piston (66) near the trigger screw (63).

3. The biomimetic folding-wing unmanned glider according to claim 1, characterized in that: The filler storage assembly (7) includes a storage tank (71), a partition plate installed in the storage tank (71), a liquid outlet opened on the mounting surface of the storage tank (71) and the explosive block (62), a liquid outlet baffle plate (73) disposed between the storage tank (71) and the explosive block (62), a stirring assembly (75) installed in the storage tank (71) for mixing and stirring the filler flowing into the liquid outlet, and a liquid outlet control assembly (74) for controlling the liquid outlet baffle plate (73) to block the liquid outlet; The partition plate divides the liquid storage tank (71) into two liquid storage chambers. The partition plate divides the liquid outlet into two parts, which are connected to the two liquid storage chambers respectively. The liquid outlet is connected to the corresponding multiple explosion chambers (65) through a first flow channel, which is located outside the propulsion piston (66).

4. The biomimetic folding-wing unmanned glider according to claim 3, characterized in that, The liquid discharge control component (74) includes: Two limiting protrusions (741) are fixedly installed at the tail of the explosion chamber (65), and the liquid outlet baffle (73) slides within the two limiting protrusions (741). The liquid discharge control gear (742) is sleeved on the trigger screw (63) and rotates with the trigger screw (63); The liquid discharge control rack (743) is disposed at one end of the liquid discharge baffle plate (73) near the actuating cylinder (61) and is connected to the liquid discharge control gear (742).

5. A biomimetic folding-wing unmanned glider according to claim 3, characterized in that: The filler includes epoxy resin and curing agent, which are respectively disposed in the two storage chambers of the storage tank (71); The stirring assembly (75) includes a stirring motor (751) installed inside the liquid storage tank (71) and a stirring paddle (752) coaxially arranged with the output shaft of the stirring motor (751); a mounting plate is provided on the partition plate, the stirring motor (751) is installed on the lower end face of the mounting plate, and the stirring paddle (752) extends into the inner cavity of the liquid outlet; The inner wall of the unfolding pipe (5) is provided with a heating wire (30) for accelerating the curing of the mixed filler.

6. The biomimetic folding-wing unmanned glider according to claim 1, characterized in that: The impact explosive (68) includes at least one of silver fulminate and mercuric fulminate.

7. The biomimetic folding-wing unmanned glider according to claim 1, characterized in that: The head (1) is detachably connected to the fuselage (2), and the head (1) is provided with an ammunition compartment (20) for storing ammunition.

8. A biomimetic folding-wing unmanned glider according to claim 1, characterized in that: The inner wall of the explosion chamber (65) is provided with a buffer layer, which is made of one of the following materials: cross-linked polyethylene, epoxy resin, or fluffy cotton.

9. A biomimetic folding-wing unmanned glider according to claim 1, characterized in that: The front end of the machine head (1) is also provided with a speed control component (8) or an infrared mapping component (9).

10. A biomimetic folding-wing unmanned glider according to any one of claims 1-9, characterized in that: The outer surfaces of the head (1), body (2) and tail (3) are coated with a thermal insulation stealth coating, which is made of one of the following: conductive polymer, cellulose aerogel coated fabric, or doped semiconductor material.

Images