Basalt fiber unmanned aerial vehicle and method of making the same

Abstract

The application belongs to the technical field of unmanned planes, and discloses a basalt fiber unmanned plane and a preparation method thereof, which comprises a body, a front plane arm, a rear plane arm and a wing arranged on the body, and a mounting assembly arranged at the bottom of the body. When the basalt fiber unmanned plane is used, a passive air pressure linkage self-adaptive adjusting structure is arranged, and no electric control components are carried and no additional power supply is needed. The flying head-on airflow is completely used as a power source. The air pressure power output can be self-adaptively completed according to the real-time flight wind speed of the unmanned plane. The translation distance and the opening angle of the guide plate relative to the front plane arm are synchronously dynamically adjusted in two dimensions. When the unmanned plane flies at a low speed, the mechanism is in a folding state, the additional aerodynamic drag is reduced, the endurance performance of the unmanned plane is ensured, the mechanism is automatically unfolded and adjusted when the unmanned plane flies at a high speed, the high-speed flow field characteristics are matched, the periodic large-scale vortex structure formed above the front plane arm is effectively broken, and the impact of the alternating wind pressure on the basalt fiber plane arm is weakened.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and more particularly to basalt fiber UAVs and their preparation methods. Background Technology

[0002] Basalt fiber drones, with their superior characteristics of high strength, high toughness, corrosion resistance and lightweight, are widely used in high-speed cruising, long-distance inspection and complex airspace operation scenarios.

[0003] In existing technologies, the front arm of a basalt fiber UAV continuously interacts with the incoming airflow and the downwash airflow from the rotor during high-speed flight, which easily forms a regular large-scale vortex structure above the arm. This type of periodic vortex structure will generate continuous alternating wind pressure impact on the arm shell, which can easily cause problems such as arm micro-flutter, structural resonance and decreased aerodynamic stability under long-term effects.

[0004] Currently, most industry improvements to suppress vortex disturbances on drone arms involve fixed-shape guide structures or single fairing structures. These structures have fixed shapes and cannot adaptively and dynamically adjust according to changes in real-time wind speed and flight speed of the drone. At low speeds, fixed guide structures generate additional parasitic drag, reducing the drone's endurance. At high speeds, fixed structures cannot match the vortex characteristics of high-speed, large-flow fields, resulting in a significant decrease in vortex suppression and flow stabilization effects, and failing to effectively mitigate vortex-induced vibration problems under high-speed conditions. Summary of the Invention

[0005] This invention addresses the technical shortcomings of existing basalt fiber UAVs, such as the tendency for eddy currents to be generated in the front arm, the inability of the fixed airflow guide structure to self-adjust, poor stability during high-speed flight, high wind resistance at low speeds, and high endurance loss. It provides a basalt fiber UAV and its manufacturing method.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: on the one hand, it provides a basalt fiber unmanned aerial vehicle, including a fuselage, a front arm and a rear arm disposed on the fuselage, wings and an assembly disposed on the bottom of the fuselage;

[0007] A mounting plate is fixed to one side of the mounting assembly, and a passive power component is provided on the mounting plate.

[0008] A mounting groove is provided on one side of the front arm, and an adjustment component is provided inside the mounting groove;

[0009] The passive power component and the regulating component are in air pressure connection;

[0010] The adjustment component includes a guide vane that can synchronously adjust the spacing and opening angle. The passive power component can adaptively output air pressure power according to the wind speed of the UAV flight, driving the guide vane to complete the spacing translation and angle deflection adjustment relative to the front arm.

[0011] Preferably, the passive power assembly includes a supporting cylinder, a bracket, a support, and a sealed cylinder that are fixedly disposed on one side of the fixed plate;

[0012] The inner wall of the bracket is provided with a drive shaft via a bearing. A turbine blade is fixedly provided at one end of the drive shaft, and a cam is fixedly provided at the other end of the drive shaft. A connecting rod is hinged to one side of the cam, and a piston plate is hinged to the bottom end of the connecting rod.

[0013] Preferably, the piston plate is movably embedded in the inner wall of the sealed cylinder, the outer surface of the sealed cylinder is symmetrically connected with an air supply pipe, the support is fixedly disposed on one side of the mounting assembly, and the sealed cylinder is fixedly disposed on one side of the support.

[0014] Preferably, the adjustment assembly includes two drive cylinders symmetrically fixed to the inner wall of the mounting groove, and a circular plate is movably embedded in the inner wall of the drive cylinder.

[0015] Preferably, a transmission push rod is fixedly connected to one side of the circular plate, a return spring is movably sleeved on the outer surface of the transmission push rod, and a hinge seat is fixedly provided at the end of the transmission push rod.

[0016] Preferably, a rocker arm is hinged to one side of the hinge seat, and a sliding base is hinged to one end of the two rocker arms. A central shaft is fixedly installed on one side of the sliding base, and two guide plates are movably sleeved on the outer surface of the central shaft. The two air supply pipes are respectively connected to the corresponding drive cylinder in a sealed manner through a connecting pipe.

[0017] Preferably, a sealing box is fixedly installed on one side of the inner wall of the mounting groove. Two push plates that can slide relative to each other are symmetrically and movably embedded in the inner wall of the sealing box. A linkage rod is fixedly installed on the outer side of the push plate. The end of the linkage rod away from the push plate is fixedly connected to the hinge seat. A square guide tube is fixedly connected to one side of the sealing box.

[0018] Preferably, a slider is movably embedded in the inner wall of the square guide tube, a control plate is fixedly installed on one side of the slider, an elastic sheet is fixedly installed between the slider and the inner wall of the square guide tube, and two round rods are symmetrically hinged to the front side of the control plate.

[0019] Preferably, a guide slide seat is fixedly installed on the side wall of the guide plate, and a sliding pin is slidably assembled on the inner wall of the guide slide seat, with the top end of the sliding pin hinged to the end of the round rod.

[0020] On the other hand, the present invention provides a method for manufacturing a basalt fiber unmanned aerial vehicle (UAV), which includes the following steps:

[0021] S1. Raw material ratio modification: Continuous basalt fiber untwisted coarse filament bundles with a single filament diameter of 9-13μm are selected as the body reinforcement substrate. Bisphenol A type epoxy resin matrix and methyltetrahydrophthalic anhydride curing agent are uniformly mixed at a mass ratio of 100:35, and 0.5% silane coupling agent is added for interface modification to prepare a highly wettable composite resin adhesive.

[0022] S2. Fiber layup molding: Basalt fiber bundles are laid up in layers in an alternating symmetrical manner of 0° / ±45° / 90°. After being fully impregnated with composite resin, the fuselage, front arm, rear arm and wing are formed by high temperature molding at 135~150℃ and 8~10MPa.

[0023] S3. Gradient curing and finishing: The initial molded body blank is subjected to a gradient high-temperature curing process, which involves pre-curing at 80℃ for 2 hours, medium-temperature curing at 120℃ for 3 hours, and high-temperature curing at 150℃ for 4 hours in sequence to gradually release the internal stress of the molding. After curing, the blank is polished, trimmed and corrected, and the dimensions are calibrated to control the dimensional tolerance of the body to ±0.05mm, thus completing the preparation of the main body.

[0024] S4. Precision machining of functional components: Separately machine each component of the passive pneumatic power component and the flow regulation component. Perform inner wall sealing grinding and airtightness enhancement treatment on the sealed cylinder, drive cylinder, sealed box and connecting pipeline. Perform curved surface polishing, noise reduction and weight reduction treatment on moving components such as turbine blades, cams, and guide vanes.

[0025] S5. Integrated and Sealed Assembly: The fixing plate is locked and fixed to the outside of the mounting assembly. The fixed support cylinder, bracket, support, and sealed cylinder are aligned and assembled to form a passive power component. The drive cylinder, sealing box, and guide plate are integrated and assembled inside the mounting groove of the front arm. The precise assembly of each hinge and sliding structure is completed. The air supply pipe and connecting pipe are sealed and connected to form a complete sealed air pressure transmission circuit.

[0026] Compared with the prior art, the advantages and positive effects of the present invention are as follows:

[0027] This invention, through the setting of a passive air pressure linkage adaptive adjustment structure, eliminates the need for electronic control components and additional power supply. It utilizes the oncoming airflow as the power source and can adaptively complete the air pressure power output according to the real-time flight wind speed of the UAV. Simultaneously, it achieves two-dimensional dynamic adjustment of the translational distance and opening angle of the guide vane relative to the front arm. During low-speed flight, the mechanism is in a retracted state, reducing additional aerodynamic drag and ensuring the UAV's endurance. During high-speed flight, it automatically expands and adjusts to match the characteristics of the high-speed flow field, effectively breaking the periodic large-scale vortex structure formed above the front arm, weakening the impact of alternating wind pressure on the basalt fiber arm, suppressing arm flutter and structural resonance, and improving the aerodynamic smoothness and structural stability of the UAV during high-speed flight. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the scene structure in an embodiment of the present invention.

[0029] Figure 2 This is a schematic diagram of the fuselage structure in an embodiment of the present invention.

[0030] Figure 3 This is a partial structural diagram of an embodiment of the present invention.

[0031] Figure 4 This is a cross-sectional view of the supporting cylinder and the sealed cylinder in an embodiment of the present invention.

[0032] Figure 5 This is a schematic diagram of the front arm in an embodiment of the present invention.

[0033] Figure 6 This is a cross-sectional view of the front arm in an embodiment of the present invention.

[0034] Figure 7 This is a cross-sectional view of the drive cylinder in an embodiment of the present invention.

[0035] Figure 8 This is an exploded view of the flow guide plate in an embodiment of the present invention.

[0036] Figure 9 This is an embodiment of the present invention. Figure 8 Enlarged structural diagram at point A in the middle.

[0037] Legend: 1. Fuselage; 101. Front arm; 102. Rear arm; 103. Wing; 104. Mounting assembly; 2. Mounting plate; 201. Support cylinder; 202. Bracket; 203. Drive shaft; 204. Turbine blade; 205. Cam; 206. Connecting rod; 207. Piston plate; 208. Support; 209. Sealed cylinder; 210. Air pipe; 3. Mounting slot; 301. Drive cylinder; 302. Circular... 303. Plate; 304. Transmission push rod; 305. Return spring; 306. Hinge seat; 307. Swing rod; 308. Sliding base; 309. Connecting pipe; 310. Central shaft; 4. Guide plate; 4. Sealing box; 401. Push plate; 402. Linkage rod; 403. Square guide tube; 404. Slider; 405. Control plate; 406. Elastic sheet; 408. Round rod; 409. Sliding pin; 410. Guide groove seat. Detailed Implementation

[0038] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0039] like Figures 1 to 9 As shown, the present invention provides a basalt fiber unmanned aerial vehicle and its manufacturing method, including a fuselage 1, a front arm 101, a rear arm 102, a wing 103 disposed on the fuselage 1, and an installation assembly 104 disposed at the bottom of the fuselage 1.

[0040] A mounting plate 2 is fixed on one side of the mounting assembly 104, and a passive power component is provided on the mounting plate 2.

[0041] A mounting groove 3 is provided on one side of the front arm 101, and an adjustment component is provided inside the mounting groove 3;

[0042] The passive power unit and the regulating unit are connected by air pressure.

[0043] The adjustment component includes a guide vane 310 that can synchronously adjust the spacing and opening angle. The passive power component can adaptively output air pressure power according to the wind speed of the UAV flight, driving the guide vane 310 to complete the spacing translation and angle deflection adjustment relative to the front arm 101.

[0044] In use, the UAV relies on the fuselage 1, front arm 101, rear arm 102, and wing 103 to maintain its overall flight attitude and aerodynamic gliding. The bottom mounting assembly 104 is used to support the external components and the entire adjustment mechanism. The fixing plate 2 provides a stable mounting reference for the passive power component. The passive power component adaptively outputs the corresponding pressure medium according to the real-time flight wind speed, and accurately delivers the pressure power to the adjustment component inside the mounting slot 3 of the front arm 101 through a closed air passage. This synchronously drives the guide plate 310 to complete horizontal translation and rotational deflection relative to the front arm 101, changing the relative distance between the guide plate 310 and the front arm 101 and the opening angle between the two guide plates 310 in real time. This adaptively matches the changes in the airflow field at different flight speeds, effectively breaking the periodic vortex structure generated above the front arm 101 and weakening the alternating impact of vortex-induced vibration on the basalt fiber arm structure.

[0045] Please see Figures 1 to 9 In one embodiment, the passive pneumatic power assembly is fixedly assembled on one side of the fixed plate 2, specifically including a supporting cylinder 201, a bracket 202, a support 208, and a sealed cylinder 209.

[0046] Specifically, the inner wall of the bracket 202 is rotatably fitted with a drive shaft 203 via bearings, allowing the drive shaft 203 to rotate stably. One end of the drive shaft 203 is fixedly mounted with a turbine blade 204, which can obtain rotational power through the scouring of the oncoming airflow. The other end of the drive shaft 203 is fixedly mounted with a cam 205, so that the turbine blade 204, the drive shaft 203 and the cam 205 rotate synchronously and coaxially. The eccentric position of the cam 205 is hinged to a connecting rod 206, and the bottom end of the connecting rod 206 is hinged to the piston plate 207, thereby converting the circular rotational motion of the cam 205 into the linear reciprocating motion of the piston plate 207.

[0047] Furthermore, the piston plate 207 is movably embedded in the inner wall of the sealed cylinder 209, and the piston plate 207 is sealed to the inner wall of the sealed cylinder 209, allowing it to slide up and down along the inner wall of the sealed cylinder 209. Two gas supply pipes 210 are symmetrically connected to the outer surface of the sealed cylinder 209 for outputting high-pressure gas to complete power transmission. The support 208 is fixedly installed on one side of the mounting assembly 104, and the sealed cylinder 209 is fixedly mounted on the support 208. The support 208 provides stable support and positioning, ensuring that the sealed cylinder 209 will not shift or shake during the reciprocating motion of the piston plate 207, thus ensuring the stability of the gas path seal.

[0048] Please see Figures 1 to 9 In one embodiment, the adjustment assembly includes two drive cylinders 301 symmetrically fixed to the inner wall of the mounting groove 3. The two drive cylinders 301 are positioned opposite each other and have the same structure, forming a double-sided symmetrical pneumatic drive structure. A circular plate 302 is movably embedded in the inner wall of each drive cylinder 301. The circular plate 302 is in a sealed sliding fit with the inner wall of the drive cylinder 301. After the high-pressure gas enters the interior of the drive cylinder 301, it can push the circular plate 302 to move axially, providing a power basis for subsequent mechanical transmission.

[0049] Please see Figures 1 to 9 In one embodiment, a transmission push rod 303 is fixedly connected to the outer end face of the circular plate 302, and the transmission push rod 303 moves axially synchronously with the circular plate 302. A return spring 304 is movably sleeved on the outer surface of the transmission push rod 303. The return spring 304 can be compressed and stored when the transmission push rod 303 moves forward, and release elastic potential energy to achieve structural reset when the air pressure is released. A hinge seat 305 is fixedly provided at the end of the transmission push rod 303 away from the circular plate 302. The hinge seat 305 serves as an intermediate transmission hinge point for connecting the subsequent rocker arm transmission structure to realize power steering transmission.

[0050] Please see Figures 1 to 9In one embodiment, a rocker arm 306 is hinged to the outer side of the hinge base 305. The ends of the symmetrically arranged rocker arms 306 are hinged to the sliding base 307, forming a double rocker arm synchronous push-pull structure. A central shaft 309 is fixedly mounted on one side of the sliding base 307. Two relatively rotatable guide plates 310 are movably sleeved on the outer surface of the central shaft 309. When the sliding base 307 translates, it can drive the central shaft 309 and the guide plates 310 to move as a whole, realizing the adjustment of the distance between the guide plates 310 and the front arm 101. The two gas supply pipes 210 are respectively connected to the connecting pipes 308. The gas supply pipes 210 are connected to the corresponding drive cylinders 301 in a sealed manner through the connecting pipes 308, realizing the stable transmission of high-pressure gas from the power end to the execution end.

[0051] Please see Figures 1 to 9 In one embodiment, a sealing box 4 is fixedly mounted on the inner wall of the mounting groove 3. The interior of the sealing box 4 is a sealed chamber structure, and two relatively sliding push plates 401 are symmetrically and movably embedded in its inner wall. A linkage rod 402 is fixedly connected to the outer side of each push plate 401. The end of the linkage rod 402 away from the push plate 401 is fixedly connected to the corresponding hinge seat 305, so that the hinge seat 305 can synchronously drive the push plate 401 to slide relatively inside the sealing box 4 during translation, compressing the gas inside the sealing box 4. A square guide tube 403 is fixedly connected to the outer side of the sealing box 4, and the pressurized gas inside the sealing box 4 can be introduced into the square guide tube 403 to provide pneumatic power for the angle adjustment mechanism.

[0052] Please see Figures 1 to 9 In one embodiment, an axially sliding slider 404 is movably embedded in the inner wall of the square guide tube 403. A control plate 405 is fixedly mounted on one side of the slider 404. An elastic sheet 406 is fixedly connected between the slider 404 and the inner wall of the square guide tube 403. The elastic sheet 406 can undergo elastic deformation as the slider 404 slides, and can also drive the slider 404 to reset by its own elasticity after the air pressure disappears. Two round rods 408 are symmetrically hinged to the front side of the control plate 405. The round rods 408 serve as intermediate transmission connectors to transmit push and pull power, thereby realizing the angle deflection action of the guide plate 310.

[0053] Please see Figures 1 to 9 In one embodiment, a guide slide seat 410 is fixedly installed on the side wall of each guide plate 310. A guide slide groove is opened inside the guide slide seat 410, and a sliding pin 409 is slidably assembled on the inner wall of the slide groove. The top end of the sliding pin 409 is hinged to the end of the corresponding round rod 408. The round rod 408 pushes and pulls the sliding pin 409 to slide along the inner trajectory of the guide slide seat 410, thereby pulling the guide plate 310 to rotate and deflect around the central axis 309, and finally realizing the adaptive adjustment of the opening and closing angle of the two guide plates 310.

[0054] It is worth noting that under different flight conditions, in low-speed flight, the oncoming airflow velocity is low, the turbine blade 204 rotates slowly, the piston plate 207 reciprocates and compresses at a low frequency, and the gas production pressure is low. The overall mechanism is insufficient to drive the various transmission components to move significantly. The guide vanes 310 remain in a small-spaced, small-angled state to minimize low-speed cruise wind resistance. In high-speed flight, the turbine blade 204 rotates at a significantly higher speed, the piston plate 207 compresses at a significantly higher frequency and the air pressure output is significantly increased, and the mechanism moves fully. Simultaneously, the spacing of the guide vanes 310 is increased and the opening and closing angle is increased, actively adapting to the vortex disturbance suppression requirements of high-speed, large-flow field.

[0055] Working principle and process: During the forward cruise flight of the UAV, the body continuously generates a high-speed relative airflow with respect to the air. The oncoming airflow continuously scours and acts on the turbine blades 204, causing the turbine blades 204 to generate continuous rotational motion under the pressure of the airflow. The faster the UAV flies, the greater the velocity of the oncoming airflow, the stronger the impact kinetic energy of the airflow on the turbine blades 204, and the higher the rotational speed. The lower the flight speed, the lower the rotational speed of the turbine blades 204. Overall, it can achieve the effect of passive power input that automatically matches the rotational frequency according to the flight airspeed.

[0056] During the continuous rotation of the turbine blade 204, the coaxially arranged cam 205 is driven to perform a synchronous circumferential rotation. The continuous rotation of the cam 205 is driven by the transmission of the connecting rod 206 to continuously drive the piston plate 207 to perform a regular up-and-down reciprocating sliding motion inside the sealed cylinder 209. In this way, the rotational mechanical energy driven by the airflow is converted into the linear reciprocating mechanical motion of the piston plate 207, providing a pneumatic power source for the subsequent pneumatic pressure regulating mechanism.

[0057] During the downward compression stroke of the piston plate 207, the sealed gas inside the sealed cylinder 209 is continuously squeezed by the piston plate 207, causing the gas pressure inside the sealed cylinder 209 to rise instantaneously, forming a high-pressure gas medium. The generated high-pressure gas is synchronously transported outward through two symmetrically arranged gas delivery pipes 210. The high-pressure gas flow is transmitted to the inside of the connecting pipe 308 through the gas delivery pipe 210, and then introduced into the two sets of drive cylinders 301 symmetrically arranged inside the mounting groove 3 through the connecting pipe 308. After the high-pressure gas enters the inside of the drive cylinder 301, it continuously pushes the circular plate 302 to move axially along the inner wall of the drive cylinder 301. The circular plate 302 synchronously drives the transmission push rod 303 to move in the same direction. During the movement, the transmission push rod 303 exerts a squeezing effect on the externally sleeved return spring 304, causing the return spring 304 to undergo compressive elastic deformation and store elastic return potential energy.

[0058] During the axial feed movement of the transmission push rod 303, the hinge seat 305 fixed at its end synchronously follows and generates linear displacement. The hinge seat 305 forms an angle push-pull motion through the hinged swing rod 306. Under the displacement action, the two sets of symmetrically arranged swing rods 306 jointly push the sliding base 307 to generate horizontal sliding. During the sliding of the sliding base 307, the central shaft 309 is synchronously translated. The guide plate 310 movably sleeved outside the central shaft 309 moves synchronously with the central shaft 309, thereby continuously changing the relative distance between the guide plate 310 and the outer wall of the front arm 101. This achieves the adaptive adjustment effect of the guide structure moving away from the arm and expanding the airflow disturbance range under high-speed conditions. It can effectively change the airflow splitting position above the arm and break up the large-scale vortex structure generated under high-speed flight conditions in advance.

[0059] At the same time, during the linear displacement process, the hinge seat 305 synchronously drives the laterally fixed linkage rod 402 to move synchronously. The linkage rod 402 extends into the sealed box 4 and drives the push plate 401 to slide relative to each other inside the sealed box 4. During the relative movement of the two push plates 401, the sealed gas inside the sealed box 4 is continuously squeezed, causing the gas pressure inside the sealed box 4 to rise rapidly. The high-pressure gas is further introduced into the cavity of the square guide tube 403, pushing the slider 404 inside the square guide tube 403 to slide along the tube guide direction. The slider 404 drives the integrated fixed control plate 405 to move synchronously.

[0060] During the feed displacement process, the slider 404 continuously pushes the elastic plate 406, causing the elastic plate 406 to undergo elastic bending deformation. During the movement of the control plate 405, the two round rods 408 hinged at the front side generate angular swing and displacement pushing and pulling actions. The sliding pin 409 hinged at the end of the round rod 408 is subjected to force and slides in a direction along the internal trajectory of the guide groove seat 410 fixed on the side of the guide plate 310. By utilizing the sliding pin 409 and the guide groove seat 410, the guide plate 310 as a whole can be pulled to rotate and deflect around the outer circular surface of the central axis 309, thereby continuously adjusting the relative opening and closing angle between the two guide plates 310, realizing the adaptive adjustment characteristic that the faster the flight speed and the higher the air pressure, the larger the opening and closing angle of the guide plate 310.

[0061] As the cam 205 continues to rotate with the turbine blade 204 and passes the maximum stroke position, the piston plate 207 enters the upward reset stroke. During the upward movement of the piston plate 207, the internal volume of the sealed cylinder 209 is gradually expanded, causing the internal air pressure of the sealed cylinder 209 to drop rapidly and be depressurized. The high pressure state inside the drive cylinder 301 is simultaneously released. At this time, the previously compressed reset spring 304 releases its stored elastic potential energy and pushes the circular plate 302 and the transmission push rod 303 to reset and slide in the opposite direction. This, in turn, drives the hinge seat 305, the swing rod 306, and the sliding base 307 to move in the opposite direction as a whole. The distance between the guide plate 310 and the front arm 101 gradually shrinks and returns to the initial small distance state.

[0062] During the reset process of the hinge seat 305, the linkage rod 402 retracts synchronously, the push plate 401 releases the pressure on the gas inside the sealed box 4, the air pressure inside the sealed box 4 drops, and the elastic plate 406 causes the slider 404 inside the square guide tube 403 to reset in the opposite direction. Through the round rod 408 and the sliding pin 409, in conjunction with the guide slide seat 410, the guide plate 310 is pulled to rotate in the opposite direction to reset, so that the opening and closing angle of the guide plate 310 is contracted to the initial small angle contact state, completing a complete air pressure drive adjustment and mechanism reset cycle.

[0063] This invention also provides a method for manufacturing a basalt fiber unmanned aerial vehicle (UAV). The UAV is manufactured using basalt fiber composite materials combined with precision mechanical assembly, and includes the following steps:

[0064] Basalt fiber body molding: Continuous basalt fiber untwisted coarse filament bundles with a single filament diameter of 9-13 μm are selected as the core reinforcing substrate. This type of basalt fiber possesses high strength, high modulus, resistance to high and low temperatures, fatigue resistance, and corrosion resistance, making it suitable for high-speed alternating load flight conditions of UAVs. It is uniformly mixed with bisphenol A type epoxy resin matrix and methyltetrahydrophthalic anhydride curing agent at a mass ratio of 100:35, and 0.5% silane coupling agent is added for interface modification to improve the wetting and bonding performance between the fiber and the resin matrix, avoiding interlayer delamination and debonding defects. The basalt fiber bundles are layered and symmetrically arranged, with a layup angle of 0° / ±45° / 90° staggered. After fully impregnating with the resin, a 135-15° angle is used. The fuselage 1, front arm 101, rear arm 102, and wing 103 are integrally molded using a high-temperature molding process at 0℃ and 8~10MPa. After molding, a gradient high-temperature curing process is adopted, first pre-curing at 80℃ for 2 hours, then medium-temperature curing at 120℃ for 3 hours, and finally high-temperature curing at 150℃ for 4 hours, gradually releasing the internal stress of molding and significantly improving the overall integrity of the fuselage structure and the interlayer bonding strength. After curing, precision grinding, trimming and correction, and dimensional calibration are carried out to strictly control the dimensional tolerance of the fuselage to ±0.05mm, ensuring the dimensional accuracy of the fuselage and the overall fatigue resistance and structural strength, effectively improving the overall structural rigidity and high-speed flight resistance to deformation, and adapting to the high-speed cruise and complex airspace flight conditions of UAVs.

[0065] Pre-fabrication of components: All parts of the passive pneumatic power component and the flow regulation component are precision machined separately. The inner walls of the sealed cylinder 209, drive cylinder 301, sealed housing 4 and all connecting pipes are sealed and polished and airtight to prevent air leakage and pressure loss. The moving components such as turbine blades 204, cams 205 and guide vanes 310 are polished and treated to reduce noise and weight to ensure smooth movement and aerodynamic performance.

[0066] Assembly and fixing of the whole machine: Lock the fixing plate 2 to the outside of the mounting assembly 104, complete the alignment and assembly of passive power components such as the supporting cylinder 201, bracket 202, support 208, and sealed cylinder 209, integrate and assemble the adjustment components such as the drive cylinder 301, sealing box 4, and guide plate 310 into the mounting groove 3 of the front arm 101, complete the precise assembly of the hinge points and sliding structure in sequence, and finally seal and connect the air supply pipe 210 and the connecting pipe 308 to form a complete and sealed pneumatic transmission circuit.

[0067] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A basalt fiber unmanned aerial vehicle (UAV), characterized in that, It includes a fuselage (1), a front arm (101), a rear arm (102), a wing (103) disposed on the fuselage (1), and a mounting assembly (104) disposed on the bottom of the fuselage (1). A mounting plate (2) is fixed to one side of the mounting assembly (104), and a passive power component is provided on the mounting plate (2); The front arm (101) has a mounting groove (3) on one side, and the mounting groove (3) is provided with an adjustment component; The passive power component and the regulating component are connected by air pressure; The adjustment component includes a guide vane (310) that can synchronously adjust the spacing and opening angle. The passive power component can adaptively output air pressure power according to the wind speed of the UAV flight to drive the guide vane (310) to complete the spacing translation and angle deflection adjustment relative to the front arm (101).

2. The basalt fiber UAV according to claim 1, characterized in that, The passive power assembly includes a support cylinder (201), a bracket (202), a support (208), and a sealed cylinder (209) fixedly disposed on one side of the fixed plate (2). The inner wall of the bracket (202) is provided with a drive shaft (203) via a bearing. One end of the drive shaft (203) is fixedly provided with a turbine blade (204), and the other end of the drive shaft (203) is fixedly provided with a cam (205). A connecting rod (206) is hinged to one side of the cam (205), and a piston plate (207) is hinged to the bottom end of the connecting rod (206).

3. The basalt fiber UAV according to claim 2, characterized in that, The piston plate (207) is movably embedded in the inner wall of the sealed cylinder (209). The outer surface of the sealed cylinder (209) is symmetrically connected with an air supply pipe (210). The support (208) is fixedly installed on one side of the mounting assembly (104). The sealed cylinder (209) is fixedly installed on one side of the support (208).

4. The basalt fiber UAV according to claim 3, characterized in that, The adjustment assembly includes two drive cylinders (301) that are symmetrically fixed to the inner wall of the mounting groove (3), and a circular plate (302) is movably embedded in the inner wall of the drive cylinder (301).

5. The basalt fiber UAV according to claim 4, characterized in that, A transmission push rod (303) is fixedly connected to one side of the circular plate (302), a return spring (304) is movably sleeved on the outer surface of the transmission push rod (303), and a hinge seat (305) is fixedly provided at the end of the transmission push rod (303).

6. The basalt fiber UAV according to claim 5, characterized in that, A rocker arm (306) is hinged to one side of the hinge seat (305), and a sliding base (307) is hinged to one end of the two rocker arms (306). A central shaft (309) is fixedly installed on one side of the sliding base (307), and two guide plates (310) are movably sleeved on the outer surface of the central shaft (309). The two air supply pipes (210) are respectively connected to the corresponding drive cylinder (301) in a sealed manner through a connecting pipe (308).

7. The basalt fiber UAV according to claim 6, characterized in that, A sealing box (4) is fixedly installed on one side of the inner wall of the mounting groove (3). Two push plates (401) that can slide relative to each other are symmetrically and movably embedded in the inner wall of the sealing box (4). A linkage rod (402) is fixedly installed on the outer side of the push plate (401). The end of the linkage rod (402) away from the push plate (401) is fixedly connected to the hinge seat (305). A square guide tube (403) is fixedly connected to one side of the sealing box (4).

8. The basalt fiber UAV according to claim 7, characterized in that, A slider (404) is movably embedded in the inner wall of the square guide tube (403). A control plate (405) is fixedly installed on one side of the slider (404). An elastic sheet (406) is fixedly installed between the slider (404) and the inner wall of the square guide tube (403). Two round rods (408) are symmetrically hinged to the front side of the control plate (405).

9. The basalt fiber UAV according to claim 8, characterized in that, The guide plate (310) is fixedly installed with a guide slide seat (410) on its side wall. The guide slide seat (410) is slidably fitted with a sliding pin (409) on its inner wall. The top of the sliding pin (409) is hinged to the end of the round rod (408).

10. A method for preparing a basalt fiber unmanned aerial vehicle, characterized in that, The basalt fiber drone according to any one of claims 1 to 9 includes the following steps: S1. Raw material ratio modification: Continuous basalt fiber untwisted coarse filament bundles with a single filament diameter of 9-13μm are selected as the body reinforcement substrate. Bisphenol A type epoxy resin matrix and methyltetrahydrophthalic anhydride curing agent are uniformly mixed at a mass ratio of 100:35, and 0.5% silane coupling agent is added for interface modification to prepare a highly wettable composite resin adhesive. S2, Fiber layup molding: Basalt fiber bundles are laid up in layers in an alternating symmetrical manner of 0° / ±45° / 90°. After being fully impregnated with composite resin, the fuselage (1), front arm (101), rear arm (102) and wing (103) are formed by high temperature molding at 135~150℃ and 8~10MPa. S3. Gradient curing and finishing: The initial molded body blank is subjected to a gradient high-temperature curing process, which involves pre-curing at 80℃ for 2 hours, medium-temperature curing at 120℃ for 3 hours, and high-temperature curing at 150℃ for 4 hours in sequence to gradually release the internal stress of the molding. After curing, the blank is polished, trimmed and corrected, and the dimensions are calibrated to control the dimensional tolerance of the body to ±0.05mm, thus completing the preparation of the main body. S4. Precision machining of functional components: Each component of the passive pneumatic power component and the flow regulation component is machined separately. The inner wall of the sealed cylinder (209), the drive cylinder (301), the sealed box (4) and the connecting pipeline are sealed and polished and the airtightness is enhanced. The moving components such as the turbine blade (204), the cam (205) and the guide plate (310) are polished and treated to reduce noise and weight. S5. Complete machine integrated sealed assembly: The fixing plate (2) is locked and fixed to the outside of the mounting assembly (104). The fixed support cylinder (201), bracket (202), support (208), and sealed cylinder (209) are aligned and assembled to form a passive power component. The drive cylinder (301), sealing box (4), and guide plate (310) are integrated and assembled in the mounting groove (3) of the front arm (101). The precise assembly of each hinge and sliding structure is completed. The air supply pipe (210) and connecting pipe (308) are sealed and connected to form a complete sealed air pressure transmission circuit.

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