Bionic folding wing unmanned gliding aircraft

Abstract

The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a bionic folding wing unmanned gliding aircraft. The unmanned aerial vehicle comprises a machine head, a machine body and a machine tail which are sequentially connected. Two folding wings and a plurality of unfolding pipelines arranged in the folding wings; an explosion power device; and two groups of filler storage assemblies. Wind power generated when the aircraft descends is used for driving the bionic tail rotor to rotate, collision explosives stored in a triggering screw rod enter an explosion bin to explode through the triggering screw rod, and the explosion thrust of the collision explosives is used for pushing a propelling piston arranged in the explosion bin to the side of an unfolding pipeline; therefore, the filling agent entering the explosion bin is extruded into the multiple unfolding pipelines, unfolding of the folding wings is achieved, the filling agent is hardened in a short time, the unfolding state of the folding wings is kept, and high heat generated by combustion of internal fuel is not needed to provide driving force; the problems that in the prior art, fuel combustion driving is large in load, and high heat is prone to being tracked are solved.

Description

Technical Field

[0001] The invention belongs to the technical field of unmanned aerial vehicles, and in particular relates to a bionic folding-wing unmanned gliding aerial vehicle. Background Art

[0002] Unmanned aerial vehicles complete set tasks under the command of humans or computers through intelligent control technology and network information systems. In recent years, unmanned aerial vehicles have been widely used in mapping and military fields, especially in the military field, when hundreds or even larger unmanned aerial vehicle formations can expand the reconnaissance and search area, and can also complete penetration or large-scale fire coverage, making existing defense means ineffective or paralyzed. In recent battlefields around the world, the application of unmanned aerial vehicles has greatly promoted the change of the war pattern.

[0003] Aircraft used in the existing military and map-making fields mostly use jet rocket engines to provide flight power. Jet rocket engines need to generate high heat through internal combustion to provide active driving force. This flight driving method has the following problems:

[0004] (1) Internal combustion generates high heat and is easily tracked and destroyed;

[0005] (2) It is necessary to place fuel inside the aircraft, which increases the weight of the aircraft, which is contrary to the requirements of lightness and flexibility of the aircraft;

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

[0007] Based on the above problems, there is an urgent need for an unmanned gliding aircraft that does not require internal combustion to provide driving force, occupies a small space, has low cost, is reliable in deployment, and has stealth. Summary of the invention

[0008] The purpose of the present invention is to overcome the defects of unmanned aerial vehicles in the prior art, such as high heat, easy tracking, large size and high cost, and to provide a bionic folding-wing unmanned gliding aircraft that does not require internal combustion, automatically unfolds its folding wings and has a large gliding distance.

[0009] The technical solution adopted by the present invention to solve the technical problem is: a bionic folding-wing unmanned gliding aircraft, comprising:

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

[0011] Two folding wings and a plurality of deployment ducts arranged in the folding wings; the folding wings are embedded and installed on the outside of the fuselage, and the deployment ducts are connected to the cavity of the fuselage;

[0012] An explosive power device is installed on the inner side of the fuselage and is used to provide power for the unfolding of the folding wings; the explosive power device includes an actuator, explosive blocks symmetrically arranged on both sides of the actuator, a threaded hole provided in the middle of the actuator, a trigger screw matched with the threaded hole, and a bionic tail rotor installed at the tail end of the trigger screw; the explosive block is provided with a plurality of explosive chambers, and a propulsion piston is provided in the explosive chamber; the trigger screw is provided with a plurality of transverse through holes for storing collision explosives; the transverse through holes correspond to the explosive chambers one by one and are connected by flow channels, and the explosive chambers correspond to the unfolding pipelines one by one and are connected by fluid channels;

[0013] Two groups of filler storage assemblies are installed at the rear end of the exploded block to provide filler to the deployment pipeline; wherein the filler storage assembly is connected to the liquid path of the explosion chamber, and when the collision explosive collides and explodes with the propulsion piston, the propulsion piston is pushed to squeeze the filler flowing into the explosion chamber into the deployment pipeline.

[0014] Furthermore, a plurality of collision protrusions are arranged on a side of the propulsion piston close to the trigger screw, and / or a carbon dioxide tank is arranged in an explosion chamber on a side of the propulsion piston close to the trigger screw.

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

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

[0017] Furthermore, the liquid outlet control component comprises:

[0018] Two limiting convex strips, both of which are fixedly arranged at the tail of the explosion chamber, and the liquid outlet blocking plate slides in the two limiting convex strips;

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

[0020] The liquid outflow control rack is arranged at one end of the liquid outflow blocking plate close to the actuating cylinder and is cooperatively connected with the liquid outflow control gear.

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

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

[0023] A heating wire for accelerating the solidification of the mixed filler is arranged on the inner wall of the deployment pipeline.

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

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

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

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

[0028] Furthermore, the outer surfaces of the nose, fuselage and tail are coated with a temperature-insulating stealth coating, and the temperature-insulating stealth coating is made of one of a conductive polymer, a cellulose aerogel coated fabric, and a doped semiconductor material.

[0029] The beneficial effects of the bionic folding-wing unmanned gliding aircraft of the present invention are:

[0030] The present invention utilizes the wind force when the aircraft descends to drive the bionic tail rotor to rotate, and uses the trigger screw to enable the collision explosive stored in the trigger screw to enter the explosion chamber and explode, and utilizes the explosive thrust of the collision explosive to push the propulsion piston provided in the explosion chamber toward the deployment pipe side, thereby squeezing the filler entering the explosion chamber into multiple deployment pipes, that is, realizing the deployment of the folding wings. The filler hardens in a short time, so that the folding wings are maintained in the deployed state. When the aircraft of the present invention is performing the folding wing deployment action, it does not need the internal fuel combustion to generate high heat to provide driving force, which solves the problem of heavy load and high heat that is easy to track caused by fuel combustion drive in the prior art. In addition, the deployment power source of the folding wings of the present invention cleverly uses the explosive thrust of the collision explosive, which greatly reduces the investment in power costs.

[0031] At the same time, the present invention designs the nose and fuselage into a detachable structure, and an ammunition magazine for loading ammunition is provided inside the nose, eliminating the need for an external ammunition magazine, thereby reducing wind resistance during flight of the aircraft. The aircraft is small in size and can fly farther, greatly increasing the application scenarios of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0033] Figure 1 It is a three-dimensional diagram of the aircraft in the first embodiment of the present invention.

[0034] Figure 2 It is a cross-sectional view of the internal structure of the aircraft in the first embodiment 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 It is a side view of the initial state of the folding wings of the aircraft in the first embodiment of the present invention before unfolding.

[0038] Figure 6 It is a partial structural schematic diagram of the aircraft in the first embodiment of the present invention.

[0039] Figure 7 It is a detailed diagram of the liquid outlet control component in the first embodiment of the present invention.

[0040] Figure 8 It is a cross-sectional view of the internal structure of the aircraft in the second embodiment of the present invention.

[0041] Fig. 9 It is a cross-sectional view of the internal structure of the aircraft in the third embodiment of the present invention.

[0042] In the figure: 1 / 1-3, nose, 2 / 2-2 / 2-3, fuselage, 3, tail, 4 / 4-2, folding wings, 5 / 5-2, unfolding pipeline, 6, explosion power device, 61, actuator, 62, explosion block, 63 / 63-2, trigger screw, 64 / 64-2, bionic tail rotor, 65 / 65-2, explosion chamber, 66 / 66-2, propulsion piston, 67, transverse through hole, 68 / 68-2, collision explosive, 7, filler storage assembly, 71, liquid storage tank, 73, liquid discharge blocking plate, 74, liquid discharge control assembly, 741, limiting convex strip, 742, liquid discharge control gear, 743, liquid discharge 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 magazine. 30. Heating wire, 40. Power supply. DETAILED DESCRIPTION

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

[0044] Embodiment 1

[0045] like Figure 1-Figure 7 The specific embodiment of the bionic folding-wing unmanned glider of the present invention shown comprises: a nose 1, a fuselage 2, a tail 3, two folding wings 4, a plurality of deployment pipes 5 arranged in the folding wings 4, an explosive power device 6, and two groups of filler storage components 7. 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. The explosive power device 6 is installed on the inner side of the fuselage 2 and is used to provide power for the unfolding of the folding wings 4. The explosive power device 6 includes an actuator 61, explosive blocks 62 symmetrically arranged on both sides of the actuator 61, a threaded hole opened in the middle of the actuator 61, a trigger screw 63 matched with the threaded hole, and a bionic tail rotor 64 installed at the tail end of the trigger screw 63. A plurality of explosive chambers 65 are opened on the explosive block 62, and a propulsion piston 66 is arranged in the explosive chamber 65. A plurality of transverse through holes 67 for storing collision explosives 68 are opened on the trigger screw 63. The transverse through holes 67 correspond one-to-one to the explosive chambers 65 and are connected to the flow channels. The explosive chambers 65 correspond one-to-one to the unfolding pipelines 5 and are connected to the fluid channels. Two groups of filler storage assemblies 7 are installed at the rear end of the explosion block 62 to provide filler to the deployment pipeline 5. It should be noted that the filler storage assembly 7 in this embodiment is connected to the liquid circuit of the explosion chamber 65. When the collision explosive 68 collides and explodes with the thrust piston 66, the thrust piston 66 is pushed to squeeze the filler flowing into the explosion chamber 65 into the deployment pipeline 5.

[0046] The aircraft of this embodiment utilizes the wind force when the aircraft descends to drive the bionic tail rotor 64 to rotate, and the collision explosive 68 stored in the trigger screw 63 is caused to enter the explosion chamber 65 and explode by triggering the screw 63. The explosive thrust of the collision explosive 68 is used to push the propulsion piston 66 set in the explosion chamber 65 toward the side of the deployment pipe 5, so that the filler entering the explosion chamber 65 is squeezed into the multiple deployment pipes 5, that is, the folding wing 4 is deployed. The filler hardens in a short time, so that the folding wing 4 is maintained in the deployed state. When the aircraft of the present invention is performing the folding wing 4 deployment action, it does not need the internal fuel combustion to generate high heat to provide driving force, which solves the problem of heavy load and high heat that is easy to be tracked due to fuel combustion driving in the prior art. In addition, the deployment power source of the folding wing 4 in this embodiment cleverly uses the explosive thrust of the collision explosive 68, which greatly reduces the investment of power cost.

[0047] In the first embodiment, in order to reduce the slight heat generated by the collision and explosion of the collision explosive 68 and make the aircraft invisible, a layer of thermal insulation stealth layer is coated on the outer surfaces of the nose 1, the fuselage 2 and the tail 3. The thermal insulation stealth layer is made of one of the materials such as conductive polymer, cellulose aerogel coated fabric, doped semiconductor, etc. In the first embodiment, a trigger screw 63 is used to trigger the collision of the collision explosive 68 to generate explosive thrust, and the setting of adding the thermal insulation stealth layer completely solves the problem that the aircraft is easy to be tracked and detected.

[0048] In order to ensure the explosive thrust of the collision explosive 68, a plurality of collision protrusions are provided on the side of the propulsion piston 66 close to the trigger screw 63 in this embodiment, so that the collision explosive 68 can fully collide with the propulsion piston 66. Furthermore, a buffer layer is provided on the inner wall of the explosion chamber 65 in this embodiment to ensure that the collision explosive 68 does not directly explode when it contacts the inner wall of the explosion chamber 65, and to ensure that the collision explosive 68 explodes only when it contacts the propulsion piston 66, that is, the pushing effect of the explosive thrust on the propulsion piston 66 can be ensured. The buffer layer in this embodiment 1 is made of one of cross-linked polyethylene, epoxy resin, and fluffy cotton materials, and is glued to the inner wall of the explosion chamber 65.

[0049] It should be further explained that the collision explosive 68 includes at least one of silver fulminate and mercury fulminate, and the collision explosive 68 in this embodiment adopts a silver fulminate rolling body. It should be understood that other explosives with collision explosion function that are not mentioned in this text and can be thought of by those skilled in the art should also be included in the protection scope of the present 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 in the liquid storage tank 71, a liquid outlet opened on the mounting surface of the liquid storage tank 71 and the explosive block 62, a liquid outlet blocking plate 73 arranged between the liquid storage tank 71 and the explosive block 62, a stirring assembly 75 installed in 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 blocking 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, which are respectively connected to the two liquid storage chambers, and the liquid outlet is connected to the corresponding multiple explosion chambers 65 through the first flow channel, and the first flow channel is located on the outside of the propulsion piston 66. In this embodiment 1, four bosses are provided below the liquid storage tank 71, and the four bosses are used to separate the liquid storage tank 71 and the explosive block 62, and reserve space for the liquid outlet blocking plate 73.

[0051] Of course, the specific structure of the filler storage assembly 7 is a preferred embodiment, and there is no absolute limitation on the structure of the filler storage assembly 7. As another embodiment, the filler storage assembly 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 channel of the explosion chamber 65. The filler in this embodiment includes epoxy resin and curing agent, which are respectively arranged in two liquid storage chambers of the liquid storage tank 71. After the epoxy resin and the curing agent are fully mixed in the flow channel and the explosion chamber 65, they are squeezed into the expansion pipe 5 and then solidified.

[0052] In order to achieve sufficient mixing of the epoxy resin and the curing agent, a stirring assembly is installed in the liquid storage tank. 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 cross plate is provided on the partition plate, the stirring motor 751 is installed on the lower end surface of the mounting cross plate, and the stirring paddle 752 extends into the inner cavity of the liquid outlet.

[0053] In order to achieve instant curing of the mixed filler entering the deployment pipe 5, thereby maintaining the deployment state of the folding wing 4, a heating wire 30 is attached to the inner wall of the deployment pipe 5, and the heating wire 30 can heat the filler entering the deployment pipe 5 to shorten the curing time and ensure the completeness of the deployment of the folding wing 4. It should be further explained that in this embodiment, the power supply 40 for providing power to the heating wire 30 and the stirring motor 451 is installed in the head 1, and the head 1 is designed as a hollow structure to facilitate the installation of the power supply 40.

[0054] See also Figure 6The liquid outlet control assembly 74 in this embodiment includes two limit convex strips 741, a liquid outlet control gear 742 and a liquid outlet control rack 743. Specifically, during installation, the two limit convex strips 741 are fixedly arranged at the tail of the explosion chamber 65, and the liquid outlet blocking plate 73 slides in the two limit convex strips 741 to control the liquid passage between the liquid outlet and the first flow channel. The liquid outlet control gear 742 is sleeved on the trigger screw 63 and rotates with the trigger screw 63. The liquid outlet control rack 743 is arranged at one end of the liquid outlet blocking plate 73 close to the actuator 61 and is connected with the liquid outlet control gear 742.

[0055] In this embodiment, three transverse through holes 67 are provided on the trigger screw 63, and three explosion chambers 65 are provided on the corresponding two explosion blocks 62. The three explosion chambers 65 on one explosion block 62 are all connected through the flow channel, and three deployment pipes 5 are arranged in parallel on a corresponding folding wing 4. When the aircraft is in the original state, the folding wing 4 is attached to the fuselage 2 around. When the trigger screw 63 is driven by the bionic tail rotor 64, it rotates counterclockwise, so that the trigger screw 63 is screwed and moved from the center tube. When the trigger screw 63 moves to the three transverse through holes 67 that are connected with the corresponding explosion chamber 65, the silver fulminate rolling body in the transverse through hole 67 enters the corresponding explosion chamber 65 under the action of the rotational force to perform a collision explosion reaction.

[0056] Specifically, when the aircraft is installed, the silver fulminate rolling body is stored in the three transverse through holes 67 of the trigger screw 63, the tail end of the trigger screw 63 passes through the tail 3 and is fixedly connected to the bionic tail rotor 64 with screws, and the bionic tail rotor 64 moves counterclockwise under the action of the 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 meshing with the liquid discharge control gear 742 is arranged on the explosion block 62, and epoxy resin and curing agent are respectively injected into the two liquid storage chambers of the liquid storage tank 71, and a propulsion piston 66 is installed in the explosion chamber 65. The operation process of the aircraft of this embodiment is as follows:

[0057] In the initial state, the two folding wings 4 of the drone are attached to the fuselage 2. Figure 5 As shown, the state of the folding wings 4 before unfolding is that the two folding wings 4 are attached to the fuselage 2 facing each other. When the aircraft descends, the folding wings 4 are detached from the fuselage 2. The wind force during descent drives the bionic tail rotor 64 to rotate, and the collision explosive stored in the trigger screw 63 enters the explosion chamber 65 and explodes through the trigger screw 63. The explosive thrust of the collision explosive is used to push the propulsion piston 66 set in the explosion chamber 65 toward the side of the deployment pipe 5, so that the filler entering the explosion chamber 65 is squeezed into multiple deployment pipes 5, that is, the fixed deployment of the folding wings 4 is achieved.

[0058] Specifically, when the drone is falling and performing free fall motion, the tail bionic tail rotor 64 begins to rotate counterclockwise under the action of the upward wind force, further driving the trigger screw 63 connected to the fuselage 2 to rotate, and the liquid discharge control gear 742 on the trigger screw 63 is meshed with the liquid discharge control rack 743. The liquid discharge control gear 742 rotates counterclockwise to drive the two liquid discharge control racks 743 to move toward the center, opening the two liquid storage tanks 71, so that the epoxy resin storage tank 71 and the curing agent storage tank 71 in the liquid storage tank 71 are opened respectively, and flow downward at the same time under the action of their own gravity, and flow into the flow channel and the explosion chamber 65 connected to the folding wing 4 in the explosion chamber 65 respectively. The three parts of silver fulminate stored in the trigger screw 63, when the bionic tail rotor 64 rotates counterclockwise and gradually separates from the main body of the fuselage 2 upward, and the epoxy resin and curing agent in the liquid storage tank 71 flow downward into the three deployment pipes 5 inside the folding wing 4, the silver fulminate and the trigger screw 6 3 rotates together and moves linearly upward at the same time. When it moves to the corresponding explosion chamber 65, the silver fulminate is thrown into the corresponding explosion chamber 65 by inertia. The inner wall of the explosion chamber 65 is provided with a buffer layer, and the corresponding propulsion piston 66 is provided with a plurality of protrusions on the surface of the side in contact with the fulminate 7. When the silver fulminate is just connected with the storage chamber, due to the existence of the buffer layer, the silver fulminate does not explode when it contacts the inner wall of the explosion chamber 65. When the silver fulminate contacts the propulsion piston 66, it explodes in the explosion chamber 65. The pressure generated by the explosion pushes the propulsion piston 66 to move toward the deployment pipe 5 side of the folding wing 4, accelerating the propulsion of the epoxy resin and the curing agent into the deployment pipe 5. The epoxy resin and the curing agent quickly fill the deployment pipe 5, so that the folding wing 4 changes from being wrapped around and attached to the main body of the fuselage 2 to a flying wing with a skeleton and fully deployed. The tail bionic tail rotor 64 is separated 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 the first embodiment of the present invention, an infrared mapping component 9 may be provided at the front end of the nose 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 reflectivity and absorption rates. The infrared sensor receiver receives the infrared rays reflected by the surface of the object and converts them into electrical signals. The terrain is mapped by processing and analyzing the received electrical signals.

[0060] Embodiment 2

[0061] The difference between the second embodiment and the first embodiment is that a carbon dioxide tank 10 is arranged in the explosion chamber 65-2 near the trigger screw 63-2. When the collision explosive 68-2 contacts the carbon dioxide tank 10, sufficient thrust is generated to push the propulsion piston 66-2 to move toward the folding wing 4-2 in the explosion chamber 65-2, so that the filler entering the explosion chamber 65-2 is fully filled into the multiple deployment pipes 5-2 in the folding wing 4-2, so that the folding wing 4-2 is fully deployed. For details, see Figure 6 .

[0062] When the trigger screw 63-2 is in the initial state, Figure 8 As shown, when the epoxy resin and the curing agent flow downward, the silver fulminate is not connected to the explosion chamber 65-2, and the initial state of the trigger screw 63-2 is shown in the figure. When the silver fulminate rolling body is connected to the explosion chamber 65-2, the epoxy resin and the curing agent have flowed into the connection between the deployment pipe 5-2 and the fuselage 2-2, and the silver fulminate rolling body hits the carbon dioxide tank 10 in the explosion chamber 65-2. The carbon dioxide tank 10 generates a huge pressure to push the thrust piston 66-2. The epoxy resin and the curing agent are accelerated to flow into the deployment pipe 5-2 under the action of the thrust piston 66-2. The epoxy resin and the curing agent are mixed and hardened in a short time. The hardened epoxy resin and curing agent mixture makes the folding wing 4-2 fixed and deployed, and the bionic tail rotor 64-2 continues to rotate and separate from the fuselage 2-2 body, and the aircraft changes from free fall to gliding motion. It should be understood that the explosion chamber 65-2 on the side of the propulsion piston 66-2 close to the trigger screw 63-2 in the second embodiment may only have a carbon dioxide tank 10, or may have a carbon dioxide tank 10 and a plurality of collision protrusions to ensure that the explosion thrust is large enough.

[0063] Embodiment 3

[0064] like Fig. 9 As shown, the difference between the third embodiment and the first embodiment or the second embodiment is that in the third embodiment, a speed control component 8 is provided at the front end of the nose 1-3, and the nose 1-3 is detachably connected to the fuselage 2-3, and an ammunition compartment 20 for storing ammunition is provided in the nose 1-3.

[0065] As an implementation method, the speed control assembly 8 of the third embodiment includes a speed controller, which is used to detect the speed of the aircraft falling and gliding, and an ammunition compartment 20 is set in the nose 1-3. When ammunition is placed in the ammunition compartment 20, it can attack the sea surface ship group, and can also attack the ground, and according to the size of the area, a suitable number of bomb-carrying gliding aircraft can be deployed. In the third embodiment, the nose 1-3 and the fuselage 2-2 are designed to be a detachable structure, and an ammunition compartment 20 for loading ammunition is set inside the nose 1-3, without the need for an external ammunition compartment, reducing the wind resistance of the aircraft during flight, and its size is small, and it can fly farther, which greatly increases the application scenarios of the aircraft.

[0066] It should be understood that the specific embodiments described above are only used to explain the present invention, and are not used to limit the present invention. Obvious changes or modifications derived from the spirit of the present invention are still within the protection scope of the present invention.

Claims

1. A bionic folding-wing unmanned gliding aircraft, characterized in that: include: A nose (1), a fuselage (2) and a tail (3) connected in sequence; Two folding wings (4) and a plurality of deployment ducts (5) arranged in the folding wings (4); the folding wings (4) are embedded and installed outside the fuselage (2), and the deployment ducts (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) and is used to provide power for the unfolding of the folding wings (4); the explosive power device (6) comprises an actuator (61), explosive blocks (62) symmetrically arranged on both sides of the actuator (61), a threaded hole provided in the middle of the actuator (61), a trigger screw (63) matched with the threaded hole, and a bionic tail rotor (64) installed at the tail end of the trigger screw (63); a plurality of explosive chambers (65) are provided on the explosive block (62), and a propulsion piston (66) is provided in the explosive chamber (65); a plurality of transverse through holes (67) for storing collision explosives (68) are provided on the trigger screw (63); the transverse through holes (67) correspond one-to-one to the explosive chambers (65) and are fluidically connected, and the explosive chambers (65) correspond one-to-one to the unfolding pipeline (5) and are fluidically connected; Two groups of filler storage components (7) are installed at the rear end of the explosive block (62) and are used to provide filler to the deployment pipeline (5); wherein the filler storage components (7) are in fluid communication with the explosion chamber (65), and when the collision explosive (68) collides and explodes with the propulsion piston (66), the propulsion piston (66) is pushed to squeeze the filler flowing into the explosion chamber (65) into the deployment pipeline (5).

2. The bionic folding-wing unmanned gliding aircraft according to claim 1, characterized in that: A plurality of collision protrusions are arranged on a side of the propulsion piston (66) close to the trigger screw (63), and / or a carbon dioxide tank (10) is arranged in an explosion chamber (65) on a side of the propulsion piston (66) close to the trigger screw (63).

3. The bionic folding-wing unmanned gliding aircraft according to claim 1, characterized in that: The filler storage assembly (7) comprises a liquid storage tank (71), a partition plate installed in the liquid storage tank (71), a liquid outlet provided on the mounting surface of the liquid storage tank (71) and the explosive block (62), a liquid outlet blocking plate (73) arranged between the liquid storage tank (71) and the explosive block (62), a stirring assembly (75) installed in 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 blocking 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, which are respectively connected to the two liquid storage chambers. The liquid outlet is connected to the corresponding multiple explosion chambers (65) through a first flow channel, and the first flow channel is located on the outside of the propulsion piston (66).

4. The bionic folding-wing unmanned gliding aircraft according to claim 3, characterized in that: The liquid outlet control component (74) comprises: Two limiting convex strips (741), the two limiting convex strips (741) are fixedly arranged at the rear of the explosion chamber (65), and the liquid outlet blocking plate (73) slides in the two limiting convex strips (741); A liquid discharge control gear (742) is sleeved on the trigger screw (63) and rotates along with the trigger screw (63); The liquid outflow control rack (743) is arranged at one end of the liquid outflow blocking plate (73) close to the actuating cylinder (61) and is connected in cooperation with the liquid outflow control gear (742).

5. The bionic folding-wing unmanned gliding aircraft according to claim 3, characterized in that: The filler comprises epoxy resin and curing agent, and the epoxy resin and curing agent are respectively arranged in two liquid storage chambers of the liquid storage tank (71); The stirring assembly (75) comprises 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 horizontal plate is arranged on the partition plate, the stirring motor (751) is mounted on the lower end surface of the mounting horizontal plate, and the stirring paddle (752) extends into the inner cavity of the liquid outlet; A heating wire (30) for accelerating the solidification of the mixed filler is arranged on the inner wall of the deployment pipe (5).

6. The bionic folding-wing unmanned gliding aircraft according to claim 1, characterized in that: The collision explosive (68) includes at least one of silver fulminate and mercury fulminate.

7. The bionic folding-wing unmanned gliding aircraft according to claim 1, characterized in that: The machine head (1) is detachably connected to the machine body (2), and an ammunition compartment (20) for storing ammunition is arranged inside the machine head (1).

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

9. The bionic folding-wing unmanned gliding aircraft 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 bionic folding-wing unmanned gliding aircraft according to any one of claims 1 to 9, characterized in that: The outer surfaces of the nose (1), the fuselage (2) and the tail (3) are coated with a temperature-insulating stealth coating, and the temperature-insulating stealth coating is made of one of a conductive polymer, a cellulose aerogel coated fabric, and a doped semiconductor material.

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