Automatic deployment structure for a square-shaped aircraft

Abstract

The present application relates to the field of aircraft technology, in particular to an automatic unfolding structure for a square nest aircraft, comprising a plurality of mutually parallel connecting rods, the two ends of the connecting rods are respectively fixedly installed with auxiliary frames, one end of the corner of the auxiliary frames on both sides is commonly connected with a mounting frame, the two sides of the mounting frame are provided with unfolding assemblies capable of extending along the length direction, the end of the unfolding assembly is installed with a tilting motor through a mounting shell, and the driving end of the tilting motor is connected with a turbofan. The present application has strong structure adaptability and flexible form, adapts to the square nest storage and multi-element use demand, has compact overall layout, and through the integrated design of the connecting rod, the auxiliary frame and the mounting frame, the square nest aircraft storage demand is met, at the same time, spring compression type, spring stretching type, worm type, telescopic rod type unfolding assemblies and various subdivided structures are provided, the shape can be flexibly selected according to the model and working condition, and the connecting rods can be arranged adjacent to or at opposite angles, which is suitable for complete or simple aircraft structure, and has excellent universality and expansibility.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and more specifically to an automatic unfolding structure for a square-nest aircraft. Background Technology

[0002] With the rapid development of aircraft technology, cuboidal aircraft, due to their advantages such as convenient storage, efficient transportation, and small footprint, have been widely used in various fields such as logistics, surveying and monitoring, and emergency rescue. One of the core requirements of cuboidal aircraft is to achieve the expansion and collapse of key flight components such as turbofans. Components can be deployed during flight to ensure flight performance, and retracted to fit the size of the cuboidal nest during storage. However, the existing turbofan expansion structures of aircraft still have many technical defects and are difficult to meet the actual needs of use.

[0003] Existing turbofan extension structures for aircraft mostly employ a single telescopic design, lacking diverse extension options. This makes them unsuitable for flexible adaptation to different requirements such as aircraft payload, operating environment, control precision, and cost budget, resulting in poor versatility. For example, some structures use only a simple telescopic rod for extension and retraction, leading to low adjustment precision, poor locking effect, and easy turbofan position deviation during flight. Other structures rely on spring return for extension, which, while simple, cannot achieve precise positioning and is unsuitable for scenarios with high control precision requirements, thus limiting the product's applicability.

[0004] In addition, the existing structure has low overall integration and low space utilization. Even after shrinking, the volume is still large, making it difficult to meet the needs of nest-like storage. Furthermore, some structures lack effective buffer protection design, making them susceptible to vibration and impact during storage, transportation, and flight, which can damage components and affect the overall reliability of the aircraft.

[0005] To address the problems of poor versatility, complex structure, insufficient operational stability, inconvenient assembly and maintenance, and poor adaptability of the existing technologies, there is a need for an automatic extension structure for the square nest aircraft that can adapt to diverse working conditions, has a simple structure, stable operation, convenient assembly, and can achieve linkage between extension, retraction, and rotation, so as to solve the defects of the existing technologies and meet the actual use needs of the square nest aircraft.

[0006] Therefore, it is necessary to invent an automatic unfolding structure for a square-nest aircraft to solve the above problems. Summary of the Invention

[0007] The purpose of this invention is to provide an automatic deployment structure for a square-nest aircraft. By designing multiple types of adaptable deployment components and a linked telescopic and rotating structure, it solves the problems of poor versatility, complex structure, inconvenient storage, and unreliable operation of existing deployment structures.

[0008] To achieve this objective, the present invention adopts the following technical solution: An automatic deployment structure for a square-nest aircraft is provided, comprising multiple parallel connecting rods. Auxiliary frames are fixedly mounted at both ends of each connecting rod. A mounting frame is connected to one end of each auxiliary frame at a corner. Deployment components capable of extending along the length direction are provided on both sides of the mounting frame. A tilting motor is mounted at the end of each deployment component via a mounting housing. A turbofan is connected to the drive end of the tilting motor. The corners of the auxiliary frames include connecting holes adapted to the connecting rods and adjusting guide holes adapted to the telescopic ends of the deployment components. The adjusting guide holes are located adjacent to or diagonally opposite the connecting holes. When the deployment component slides along the length direction of the mounting frame, the turbofan rotates along the axis of the deployment component.

[0009] As a preferred embodiment of an automatic deployment structure for a square-nest aircraft, the deployment component includes a spring-compression deployment component. The mounting frame has installation pipes at both ends, and spring slots are provided at both ends of the installation pipes. The position of the installation pipes corresponds to the position of the adjustment guide holes. The spring-compression deployment component is slidably installed inside the installation pipes. The spring-compression deployment component includes a compression spring, which is connected to the spring slots.

[0010] As a preferred embodiment of an automatic deployment structure for a square-nest aircraft, the deployment component includes a worm gear type deployment component. Installation pipes are provided at both ends of the mounting frame, and turbine slots are opened at both ends of the installation pipes. The worm gear type deployment component includes an adjusting worm. A transmission turbine with a servo motor is fixedly mounted on the end face of the mounting frame. The transmission turbine meshes with the adjusting worm through the turbine slots. An inner helical groove is opened on the inner side of the installation pipe, and a guide post four that slides along the inner helical groove is fixedly connected to the outer side of the adjusting worm.

[0011] As a preferred embodiment of an automatic deployment structure for a square-nest aircraft, the deployment component includes a telescopic rod type deployment component. The mounting frame has mounting slots on both sides. The fixed end of the telescopic rod type deployment component is installed inside the mounting slot. The telescopic end of the telescopic rod type deployment component is slidably connected to the adjustment guide hole.

[0012] As a preferred embodiment of an automatic deployment structure for a square-nest aircraft, the deployment component includes a spring-tensioned deployment component. The mounting frame has installation pipes at both ends, and tension springs are installed inside the installation pipes. The spring-tensioned deployment component includes deployment rods with various cross-sections. The two ends of the tension springs are respectively engaged with the deployment rods. The deployment rods include prismatic deployment rods with an overall spiral shape, plum blossom-shaped deployment rods, and rod-groove-shaped deployment rods with spiral grooves on their bodies. The auxiliary frame has adjustment guide holes adapted to the cross-section of the deployment rods.

[0013] As a preferred embodiment of an automatic deployment structure for a square-nest aircraft, the spring-compression deployment assembly includes various adjusting rods with different cross-sections. One end of the compression spring is fixedly connected to the adjusting rod. The adjusting rod includes a grooved adjusting rod, a plum blossom-shaped adjusting rod, and a rhombus-shaped adjusting rod. The plum blossom-shaped and rhombus-shaped adjusting rods are spiral-shaped. The outer side of the grooved adjusting rod has an outer spiral groove. The auxiliary frame has an adjustment guide hole that matches the cross-section of the adjusting rod. When the adjusting rod is a grooved adjusting rod, a guide post extending to the inner side of the outer spiral groove is installed on the inner side of the adjustment guide hole.

[0014] As a preferred embodiment of an automatic unfolding structure for a square-nest aircraft, the adjusting rod further includes a toothed adjusting rod, an inner spiral groove is provided on the inner side of the installation pipe, and a guide post two that can slide along the inner spiral groove is fixedly installed at the end of the toothed adjusting rod.

[0015] As a preferred embodiment of an automatic deployment structure for a square-nest aircraft, a telescopic outer tube is snapped into the inner side of the mounting slot, and a limit block is provided on the end face of the mounting slot. Various inner push rods with different cross-sections are slidably connected to the inner side of the telescopic outer tube. The inner push rods include prismatic inner push rods, plum blossom-shaped inner push rods, and circular inner push rods. The auxiliary frame is provided with adjustment guide holes that are adapted to the cross-section of the inner push rods, and a tilting motor is connected to the end face of the inner push rods.

[0016] As a preferred embodiment of an automatic deployment structure for a square-nest aircraft, the mounting frame is provided with mounting pipes at both ends, and an inner spiral groove is provided on the inner side of the mounting pipe. The telescopic rod type deployment component also includes a cylindrical outer push tube and a cylindrical inner push rod. The cylindrical inner push rod is fixedly installed on the inner side of the mounting pipe, and a guide post three that can slide along the inner spiral groove is installed on the outer side of the cylindrical outer push tube.

[0017] As a preferred embodiment of an automatic deployment structure for a square-nest aircraft, a frame is mounted on the outer side of the mounting frame, a fairing is mounted on the end face of the auxiliary frame, and a wing assembly is mounted on the outer side of the frame. The wing assembly includes a side wing body. The mounting frame has a guide groove, and oblique grooves are formed on both sides of the guide groove. A guide shaft is provided in the guide groove, and a guide connecting shaft is slidably arranged inside the guide groove. The two side wing bodies are hinged to the guide connecting shaft. A wing connecting shaft that slides along the oblique groove is provided at the top of the side wing body. A torsion spring is connected to the guide connecting shaft and the two wing connecting shafts on both sides. A tail motor and a torsion spring are hinged to the connecting rod. The drive end of the tail motor is connected to the tail wing body, and the two ends of the torsion spring are respectively connected to the tail motors on both sides. When the side wing body is in the retracted state, the wing connecting shaft is near the far end of the oblique through groove, and the torsion spring is in a torsional state; when the side wing body is in the deployed state, the wing connecting shaft is near the near end of the oblique through groove, and the torsion spring is in a non-stressed state.

[0018] The beneficial effects of this invention are: strong structural adaptability and flexible form, suitable for nest storage and diverse usage needs, compact overall layout, and integrated design of connecting rods, auxiliary frames and mounting frames to meet the storage needs of nest aircraft. At the same time, it provides a variety of extension components and subdivided structures such as spring compression type, spring extension type, worm gear type and telescopic rod type, which can be flexibly selected according to the aircraft type and working conditions. The connecting rods can be arranged adjacently or diagonally, adapting to complete or simple aircraft structures, with excellent versatility and expandability.

[0019] The telescopic and rotation linkage is integrated, which simplifies the structure and ensures reliable operation. There is no need to add an additional rotation drive mechanism. By adjusting the structure of guide holes, spiral grooves and guide columns, the telescopic components can be extended and retracted while driving the turbofan to rotate synchronously. This not only simplifies the overall structure and reduces weight and energy consumption, but also ensures smooth operation and no deviation through multiple limit and guide designs, thereby improving the flight stability of the aircraft and the service life of the equipment. Attached Figure Description

[0020] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the embodiments of the present invention will be briefly described below. Obviously, the drawings described below are merely some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without any creative effort.

[0021] Figure 1 This is a schematic diagram of the structure of the aircraft with wing components of the present invention in its extended state.

[0022] Figure 2 This is a simplified assembly diagram of the aircraft in its extended state according to the present invention.

[0023] Figure 3 This is an assembly diagram of the aircraft with the prismatic adjustment rod spring extension structure of the present invention.

[0024] Figure 4 This is the present invention. Figure 3 Enlarged structural diagram at point A in the middle.

[0025] Figure 5 This is a schematic diagram of the structure of the aircraft with the rod groove type adjustment rod spring extension structure of the present invention.

[0026] Figure 6 This is a schematic diagram of the aircraft structure with a plum blossom-shaped adjusting rod spring extension structure according to the present invention.

[0027] Figure 7 This is a schematic diagram of the structure of the aircraft with the toothed adjustment rod spring extension structure of the present invention.

[0028] Figure 8 This is the present invention. Figure 7 Enlarged structural diagram at point B.

[0029] Figure 9 This is a schematic diagram of the spring slot structure of the mounting frame of the present invention.

[0030] Figure 10 This is a schematic diagram of the aircraft structure with a worm-type extension component according to the present invention.

[0031] Figure 11 This is a schematic diagram of the structure at the connection between the adjusting worm and the transmission turbine of the present invention.

[0032] Figure 12 This is the present invention. Figure 11 Enlarged structural diagram at point C.

[0033] Figure 13 This is a schematic diagram of the aircraft structure with the prismatic inner push rod extension structure of the present invention.

[0034] Figure 14 This is the present invention. Figure 13 Enlarged structural diagram at point D.

[0035] Figure 15 This is a schematic diagram of the aircraft structure with a plum blossom-shaped telescopic rod extension structure according to the present invention.

[0036] Figure 16 This is a schematic diagram of the aircraft structure with the columnar inner push rod extension structure of the present invention.

[0037] Figure 17 This is a schematic diagram of the aircraft structure with the columnar external thrust tube extension structure of the present invention.

[0038] Figure 18 This is a schematic diagram of the structure of the spring-tensioned stretching component with a prismatic stretching rod of the present invention.

[0039] Figure 19 This is the present invention. Figure 18 Enlarged structural diagram at point E in the middle.

[0040] Figure 20 This is a schematic diagram of the spring-tensioned stretching assembly with a rod-groove-shaped stretching rod of the present invention.

[0041] Figure 21 This is a schematic diagram of the spring-tensioned stretching assembly with plum blossom-shaped stretching rods of the present invention.

[0042] Figure 22This is a schematic diagram of the structure of the square nest aircraft with wing components according to the present invention.

[0043] Figure 23 This is a schematic diagram of the wing assembly structure of the present invention.

[0044] Figure 24 This is a schematic diagram of the explosive assembly of the Fangchao aircraft of the present invention.

[0045] Figure 25 This is a schematic diagram of the structure of the wing assembly of the present invention in its extended state.

[0046] In the picture: 1. Frame; 2. Mounting frame; 201. Mounting pipe; 202. Inner spiral groove; 203. Spring slot; 204. Turbine slot; 205. Limiting block; 206. Mounting slot; 3. Turbine fan; 4. Tilting motor; 5. Draft shield; 6. Auxiliary frame; 601. Connecting hole; 602. Adjustment guide hole; 7. Spring compression type extension assembly; 701. Rod groove type adjusting rod; 7011. External spiral groove one; 7012. Guide post one; 702. Plum blossom shaped adjusting rod; 703. Prism-shaped adjusting rod; 704. Toothed rod type adjusting rod; 7041. Guide post two; 710. Compression spring; 8. Telescopic rod type extension assembly; 801. Telescopic outer tube; 802. Prism-shaped inner push rod; 803. Plum blossom-shaped inner push rod; 804. Circular inner push rod; 805. Cylindrical outer push tube; 806. Cylindrical inner push rod; 807. Guide post three; 9. Worm gear extension assembly; 901. Adjusting worm gear; 902. Guide post four; 903. Transmission worm; 904. External helical groove two; 10. Connecting rod; 11. Wing assembly; 1101. Guide slot; 1102. Angled slot; 1103. Wing connecting shaft; 1104. Torsion spring one; 1105. Guide connecting shaft; 1106. Guide shaft; 1107. Tail fin body; 1108. Tail fin motor; 1109. Torsion spring two; 1110. Side wing body; 12. Spring-tensioned stretching assembly; 1201. Tension spring; 1202. Prism-shaped stretching rod; 1203. Rod-groove-shaped stretching rod; 1204. Plum blossom-shaped stretching rod. Detailed Implementation

[0047] The technical solution of the present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0048] The accompanying drawings are for illustrative purposes only and are schematic diagrams, not actual images. They should not be construed as limiting the scope of this patent. To better illustrate the embodiments of the present invention, some components in the drawings may be omitted, enlarged, or reduced, and do not represent the actual dimensions of the product. It is understandable to those skilled in the art that some well-known structures and their descriptions may be omitted in the drawings.

[0049] In the accompanying drawings of the embodiments of the present invention, the same or similar reference numerals correspond to the same or similar components. In the description of the present invention, it should be understood that if terms such as "upper," "lower," "left," "right," "inner," and "outer" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, they are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, the terms used to describe positional relationships in the drawings are only for illustrative purposes and should not be construed as limiting the present patent. For those skilled in the art, the specific meaning of the above terms can be understood according to the specific circumstances.

[0050] This invention mainly includes three core embodiments: a spring-compression type stretching component 7, a worm gear type stretching component 8, and a telescopic rod type stretching component 9. These can be combined into various sub-embodiments. Each embodiment includes multiple parallel connecting rods 10. Auxiliary frames 6 are fixedly mounted at both ends of each connecting rod 10. A mounting frame 2 is connected to one end of the corner of each auxiliary frame 6 on both sides. Stretching components extending along the length direction are provided on both sides of the mounting frame 2. A tilting motor 4 is mounted at the end of each stretching component via a mounting housing. A turbofan 3 is connected to the drive end of the tilting motor 4. The corner of the auxiliary frame 6 includes a connecting hole 601 adapted to the connecting rod 10 and an adjusting guide hole 602 adapted to the telescopic end of the stretching component. When the stretching component slides along the length direction of the mounting frame 2, the turbofan 3 rotates along the axis of the stretching component. The adjusting guide hole 602 is located adjacent to or diagonally opposite the connecting hole 601. Figure 1 and Figure 2 The diagram shows the structure of the aircraft in its extended state when the connecting rods 10 are in different positions. When multiple connecting rods 10 are adjacent, the wing assembly 11 is installed on the outer side of the frame 1. When the connecting rods 10 are diagonally arranged, it is a combined structure of a simple aircraft.

[0051] Core Implementation Example 1; Spring-Compression Type Extension Component 7; Reference Figure 9The stretching component includes a spring-compression stretching component 7. The mounting frame 2 has mounting pipes 201 at both ends. The mounting pipes 201 have spring slots 203 at both ends. The position of the mounting pipes 201 corresponds to the position of the adjustment guide hole 602. The spring-compression stretching component 7 is slidably installed on the inner side of the mounting pipes 201. The spring-compression stretching component 7 includes a compression spring 710. The compression spring 710 is hung and connected to the spring slots 203.

[0052] Detailed Example 1; Prism-shaped adjusting rod spring extension structure; refer to Figures 3 to 4 The adjusting rod is a prismatic adjusting rod 703, which is spiral in shape. A compression spring 710 is sleeved on the outside of the prismatic adjusting rod 703. The auxiliary frame 6 has an adjusting guide hole 602 that matches the cross-section of the prismatic adjusting rod 703. One end of the compression spring 710 is fixed to the prismatic adjusting rod 703. The spring reset drives the prismatic adjusting rod 703 to slide along the installation pipe 201. The spiral prismatic structure cooperates with the adjusting guide hole 602, so that the adjusting rod slides and rotates synchronously, driving the turbofan 3 to rotate.

[0053] The spiral-shaped prismatic cross-section rod, with its non-circular cross-section and precise positioning via the 602 adjustment guide hole, effectively prevents circumferential swaying and offset during extension and retraction. The spiral shape, combined with the guide hole, enables sliding rotation. The integrated structure offers excellent wear resistance and superior stability during long-term reciprocating extension and retraction.

[0054] Detailed Example 2; Plum blossom-shaped adjusting rod spring extension structure; refer to Figure 6 The adjusting rod is a plum blossom-shaped adjusting rod 702, which is spiral in shape. The auxiliary frame 6 has an adjusting guide hole 602 that matches the cross-section of the plum blossom-shaped adjusting rod 702. One end of the compression spring 710 is fixed to the plum blossom-shaped adjusting rod 702. The extension and retraction of the spring causes the plum blossom-shaped adjusting rod 701 to slide along the installation pipe 201. Because the adjusting rod is spiral in shape and matches the adjusting guide hole 602, the plum blossom-shaped adjusting rod 702 rotates synchronously during the sliding process, causing the turbofan 3 to rotate along the axis.

[0055] The plum blossom-shaped multi-petal cross-section has a large contact limiting area, high guiding accuracy, uniform force distribution, and strong anti-torsion performance; the spiral integrated forming structure ensures smooth and uninterrupted movement, and can stably achieve adaptive adjustment of the turbofan's 3-angle, improving the adaptability to flight airflow.

[0056] Detailed Example 3; Toothed Adjustment Rod Spring Extension Structure; refer to Figures 7 to 8The adjusting rod is a toothed adjusting rod 704; an inner spiral groove 202 is provided on the inner side of the installation pipe 201, and a guide post 7041 that can slide along the inner spiral groove 202 is fixedly installed at the end of the toothed adjusting rod 704; the auxiliary frame 6 is provided with an adjusting guide hole 602 that matches the cross section of the toothed adjusting rod 704; one end of the compression spring 710 is fixed to the toothed adjusting rod 704. When the adjusting rod slides along the installation pipe 201, the guide post 7041 slides along the inner spiral groove 202, driving the toothed adjusting rod 704 to rotate, and thus driving the turbofan 3 to rotate along the axis.

[0057] Relying on the end guide post and the inner spiral groove 202 for guiding transmission, the motion trajectory is precise and controllable with low transmission loss; the rod tooth structure has a good limiting effect, which can avoid excessive extension and retraction, and the structure has strong load-bearing capacity, making it suitable for use in heavy-load aircraft.

[0058] Detailed Example 4; Rod-type Adjusting Rod Spring Extension Structure; refer to Figure 5 The adjusting rod is a grooved adjusting rod 701, with an outer spiral groove 7011 on its outer side. The auxiliary frame 6 has an adjusting guide hole 602 that matches the cross-section of the grooved adjusting rod 701, and a guide post 7012 extending to the inner side of the outer spiral groove 7011 is installed inside the adjusting guide hole 602. One end of the compression spring 710 is fixed to the grooved adjusting rod 701. When the grooved adjusting rod 701 slides along the installation pipe 201, the guide post 7012 slides along the outer spiral groove 7011, causing the grooved adjusting rod 701 to rotate synchronously, thereby driving the turbofan 3 to rotate.

[0059] With the external spiral groove 7011 and the internal guide post 7012 embeddedly engaged, the guide stroke is long and the movement is smooth; the structure is easy to disassemble and assemble, the replacement of parts is simple, the compatibility is strong, and it is easy to mass-produce and modify.

[0060] Core Embodiment 2; Worm Gear Extension Component 9; The mounting frame 2 has mounting pipes 201 at both ends, and turbine slots 204 are opened at both ends of the mounting pipes 201. The worm gear extension component 9 includes an adjusting worm 901. A transmission turbine 903 with a servo motor is fixedly installed on the end face of the mounting frame 2. The transmission turbine 903 meshes with the adjusting worm 901 through the turbine slots 204. Detailed Example 5; Internal Helical Worm Gear Structure; refer to Figure 10 , 11Up to 12, the internal helical worm gear structure includes an internal helical groove 202 formed inside the installation pipe 201. A guide post 902, which slides along the internal helical groove 202, is fixedly connected to the outer surface of the adjusting worm gear 901. A tilting motor 4 is mounted at the end of the adjusting worm gear 901 through the installation housing. The drive end of the tilting motor 4 is connected to the turbofan 3. A servo motor drives the transmission turbine 903 to rotate, causing the adjusting worm gear 901 to slide along the installation pipe 201. The guide post 902 slides along the internal helical groove 202, causing the adjusting worm gear 901 to rotate synchronously, thereby driving the turbofan 3 to rotate along its axis.

[0061] The telescopic rotation is achieved by using the guide post 902 in conjunction with the inner spiral groove 202, which ensures smooth power transmission and a wide speed range, meeting the adjustment needs of aircraft in multiple attitudes and flight modes. The worm gear has a reverse self-locking characteristic, strong wind resistance, and greatly improves flight safety.

[0062] Detailed Example Six: External Helical Worm Gear Structure; refer to Figure 22-25 The external helical worm gear structure includes an external helical groove 904 formed on the outside of the adjusting worm 901. The auxiliary frame 6 has an adjusting guide hole 602 adapted to the cross-section of the adjusting worm 901. A locking block that can extend to the inside can also be installed on the outside of the mounting pipe 201. The locking block can engage with the end of the adjusting worm 901 in its extended state. The smooth guiding rotation is achieved by the cooperation of the external helical groove 904 and the guide hole 602, making the motion transmission smoother. The external locking block can lock and limit the end of the fully extended adjusting worm 901, effectively locking the worm's extended position and improving the locking stability and overall structural rigidity of the extended structure.

[0063] Core Implementation Example 3; Reference Figure 13 The system includes a telescopic rod-type extension component 8. The mounting frame 2 has mounting slots 206 on both sides. The fixed end of the telescopic rod-type extension component 8 is installed inside the mounting slots 206. The telescopic end of the telescopic rod-type extension component 8 is slidably connected to the adjustment guide hole 602. A tilting motor 4 is mounted on the end of the telescopic rod-type extension component 8 through a mounting housing. The drive end of the tilting motor 4 is connected to a turbofan 3. When the extension component slides, it drives the turbofan 3 to rotate along its axis. Various irregularly shaped internal push rods and tubular telescopic structures are available, allowing for flexible selection based on installation space and load requirements. This makes it suitable for different sizes and specifications of square-shaped aircraft, resulting in a wider product compatibility.

[0064] Detailed Embodiment Seven; Prism-shaped inner push rod telescopic rod extension structure; refer to Figures 13 to 14The system consists of a telescopic outer tube 801 and a rhomboid inner push rod 802. The telescopic outer tube 801 is snapped into the inner side of the mounting slot 206, and the rhomboid inner push rod 802 is slidably connected to the inner side of the telescopic outer tube 801. The auxiliary frame 6 has an adjustment guide hole 602 that matches the cross-section of the rhomboid inner push rod 802. The end face of the rhomboid inner push rod 802 is connected to the tilting motor 4. When the rhomboid inner push rod 802 slides along the telescopic outer tube 801, the rhomboid cross-section matches the adjustment guide hole 602, causing the rhomboid inner push rod 802 to rotate synchronously, thereby driving the turbofan 3 to rotate.

[0065] It adopts a prismatic non-circular cross-section for limiting, which has excellent anti-rotation effect and smooth telescopic sliding without jamming; the structure is wear-resistant and has high torsional strength, and it is not easily deformed by long-term high-frequency stretching and storage, resulting in a long service life.

[0066] Detailed Example 8: Plum blossom-shaped inner push rod telescopic rod extension structure; refer to Figure 15 The system includes a telescopic outer tube 801 and a plum blossom-shaped inner push rod 803. The telescopic outer tube 801 is snapped into the inner side of the mounting slot 206, and the plum blossom-shaped inner push rod 803 is slidably connected to the inner side of the telescopic outer tube 801. The auxiliary frame 6 has an adjustment guide hole 602 that matches the cross section of the plum blossom-shaped inner push rod 803. The end face of the plum blossom-shaped inner push rod 803 is connected to the tilting motor 4. When the plum blossom-shaped inner push rod 803 slides along the telescopic outer tube 801, the plum blossom-shaped cross section cooperates with the adjustment guide hole 602, driving the plum blossom-shaped inner push rod 803 to rotate synchronously, thereby driving the turbofan 3 to rotate.

[0067] Detailed Example 9; Circular Inner Push Rod Telescopic Rod Extension Structure; refer to Figure 16 It includes a telescopic outer tube 801 and a circular inner push rod 804; the telescopic outer tube 801 is engaged with the inner side of the mounting slot 206, and the circular inner push rod 804 is slidably connected to the inner side of the telescopic outer tube 801; the auxiliary frame 6 has an adjustment guide hole 602 that matches the cross-section of the circular inner push rod 804; the end face of the circular inner push rod 804 is connected to a tilting motor 4. When the circular inner push rod 804 slides along the telescopic outer tube 801, the limiting action of the adjustment guide hole 602 drives the circular inner push rod 804 to rotate synchronously, thereby driving the turbofan 3 to rotate. Its structure is regular, its processing and forming are simple, and its production cost is low; it is suitable for conventional installation spaces, has the strongest versatility, and is suitable for use with standardized mass-produced models.

[0068] Detailed Example 10: Columnar external push tube telescopic rod extension structure; refer to Figure 17The system includes a cylindrical outer push tube 805, a cylindrical inner push rod 806, and a guide post 807. Installation pipes 201 are installed at both ends of the mounting frame 2, and an inner spiral groove 202 is formed on the inner side of each installation pipe 201. The cylindrical inner push rod 806 is fixedly installed inside the installation pipe 201, and the cylindrical outer push tube 805 is sleeved on the outer side of the cylindrical inner push rod 806. The guide post 807 is installed on the outer side of the cylindrical outer push tube 805 and can slide along the inner spiral groove 202. A tilting motor 4 is connected to the end of the cylindrical outer push tube 805. When the cylindrical outer push tube 805 slides along the cylindrical inner push rod 806, the guide post 807 slides along the inner spiral groove 202, causing the cylindrical outer push tube 805 to rotate synchronously, thereby causing the turbofan 3 to rotate along its axis.

[0069] The pipe features an internal spiral groove and a guide post 3807 for excellent protection, preventing dust accumulation and impact damage to the external structure. The tubular telescopic structure offers a high level of protection and excellent sealing, making it suitable for operation in complex and harsh environments.

[0070] Core Implementation Example 4; Reference Figure 18-21 Spring-tensioned stretching assembly; The mounting frame 2 has mounting pipes 201 at both ends, and a tension spring 1201 is installed inside the mounting pipe 201. The two ends of the tension spring 1201 are respectively engaged with the extension rod to realize tension driving and reset. The corner of the auxiliary frame 6 includes a connecting hole 601 adapted to the connecting rod 10, and an adjustment guide hole 602 adapted to the cross section of the extension rod of the spring tension extension assembly 12. The adjustment guide hole 602 is located adjacent to or diagonally opposite the connecting hole 601.

[0071] Detailed Example 11: Prism-shaped stretching rod spring tension structure; Reference Appendix Figure 18-19 The extension rod is a helical prismatic extension rod 1202. The auxiliary frame 6 has an adjustment guide hole 602 that matches the cross section of the prismatic extension rod 1202. The two ends of the tension spring 1201 are respectively snapped and fixed to the prismatic extension rod 1202. When the aircraft is launched, the two ends of the tension spring 1201 contract inward synchronously, and the prismatic extension rod 1202 slides along the installation pipe 201. Because the prismatic extension rod 1202 is helical in shape and precisely matches the adjustment guide hole 602, the prismatic extension rod 1202 rotates synchronously during the sliding process, thereby driving the turbofan 3 to rotate along the axis, realizing the extension and attitude adjustment of the turbofan 3. After the contraction is completed, the tilting motor 4 at the end of the extension rod abuts against the auxiliary frame 6.

[0072] Detailed Example Twelve: Plum blossom-shaped stretching rod spring tension structure; Reference Appendix Figure 21The extension rod is a spiral-shaped plum blossom-shaped extension rod 1204. The auxiliary frame 6 has an adjustment guide hole 602 that matches the cross section of the plum blossom-shaped extension rod 1204. The two ends of the tension spring 1201 are respectively engaged with the plum blossom-shaped extension rod 1204. When the tension spring 1201 contracts inward synchronously, it drives the plum blossom-shaped extension rod 1204 to slide along the installation pipe 201. The spiral plum blossom-shaped structure cooperates with the adjustment guide hole 602 to make the extension rod rotate synchronously while sliding, thereby driving the turbofan 3 to rotate and ensuring that the turbofan attitude is adapted to the flight requirements.

[0073] Detailed Example Thirteen: Rod-groove Extended Rod Spring Tension Structure; Reference Appendix Figure 20 The extension rod is a grooved extension rod 1203 with a spiral groove on its body; the auxiliary frame 6 has an adjustment guide hole 602 that matches the cross-section of the grooved extension rod 1203. A guide post extending to the inner side of the spiral groove of the grooved extension rod 1203 is installed inside the adjustment guide hole 602. The original guide post structure can be used to adapt to the spiral groove size; the two ends of the tension spring 1201 are respectively engaged with the grooved extension rod 1203. When the grooved extension rod 1203 slides along the installation pipe 201 under the drive of the tension spring 1201, the guide post slides along the spiral groove, causing the grooved extension rod 1203 to rotate synchronously, thereby causing the turbine fan 3 to rotate along the axis, realizing precise linkage.

[0074] Detailed Example Fourteen: Telescopic Structure of Wing Assembly; refer to Figure 22-25 Based on the basic structures of various subdivided embodiments such as spring type, worm gear type, telescopic rod type, and spring extension type, this embodiment addresses the pain points of wing storage and deployment of the Fangchao aircraft by designing an integrated, adaptive linkage wing component telescopic structure, which solves the technical defects of the prior art such as the disconnect between wing extension and fuselage extension, large storage volume, poor deployment stability, and complex structure. A frame 1 is mounted on the outer side of the mounting frame 2. A fairing 5 is mounted on the end face of the auxiliary frame 6. A wing assembly 11 is mounted on the outer side of the frame 1. The wing assembly 11 includes a side wing body 1110. The mounting frame 2 has a guide groove 1101. Oblique grooves 1102 are formed on both sides of the guide groove 1101. A guide shaft 1106 is provided in the guide groove 1101. A guide connecting shaft 1105 is slidably arranged inside the guide groove 1101. The two side wings... The main body 1110 and the guide connecting shaft 1105 are hinged together. The top of the side wing main body 1110 is provided with a wing connecting shaft 1103 that slides along the oblique through groove 1102. The guide connecting shaft 1105 and the two wing connecting shafts 1103 are connected by a torsion spring 1104. The connecting rod 10 is hinged to the tail wing motor 1108 and the torsion spring 1109. The driving end of the tail wing motor 1108 is connected to the tail wing main body 1107. The two ends of the torsion spring 1109 are respectively connected to the tail wing motors 1108 on both sides. When the wing assembly 11 is in the retracted state, the tail fin body 1107 is folded and retracted simultaneously, at which time the second torsion spring 1109 is under torsional stress. When the wing assembly 11 is deployed, the second torsion spring 1109 releases elastic potential energy simultaneously, driving the tail fin motors 1108 on both sides to rotate around the hinge point of the connecting rod 10, realizing the automatic deployment of the tail fin body 1107, and the two tail fins are linked synchronously to ensure symmetrical deployment attitude. No additional control is required, realizing the linkage deployment of "wing-tail", solving the problem that the wings and tail fins need to be controlled separately and the deployment is not synchronized in the existing technology, improving flight stability and ease of operation.

[0075] When the Fangchao aircraft needs to be fitted with wings to improve its flight performance, refer to Figure 25 By opening guide slots 1101 and oblique slots 1102 in the mounting frame 2, and applying torsional force through torsion spring 1104, the side wing body 1110 can automatically extend after the aircraft is launched by changing the relative position of the guide connecting shaft 1105 and the wing connecting shaft 1103. This sliding deployment mechanism makes the final deployed width of the wing much greater than its retracted width in the frame, thereby achieving better flight aerodynamic performance while ensuring a small retracted volume.

[0076] When a Fangchao aircraft needs to have wings added to improve its flight performance, it can also refer to Figure 1 By setting multiple rotatable side wing bodies 1110 and tail wing bodies 1108, the wings will be extended by twisting motors after the aircraft is launched, improving the flight effect.

[0077] The aircraft has a square overall shape, and its shape fits the empty slot of the launch bay when stowed. The shape of the aircraft can be adjusted according to actual needs to meet different usage scenarios. When the aircraft is ejected, the tail fin body 1107 can be quickly deployed under the action of the torsion spring 1109, improving stability during the ejection process.

[0078] By combining different extension structures with the wing assembly 11, the extension assembly and the wing assembly 11 work together to achieve synchronous retraction and deployment of the turbofan 3, tail fin body 1107, and side wing body 1110. At the same time, it folds up as a whole during storage, with a neat and compact shape, greatly reducing the space occupied by the whole machine, which is perfectly suitable for the use of nest-sealed storage, vehicle transportation, and cluster deployment. During flight operations, it unfolds synchronously without the need for step-by-step operation, with faster response and higher degree of automation, solving the drawbacks of traditional aircraft turbofan and wing control, asynchronous deployment, and large storage volume.

[0079] The extended structure relies on mechanical guidance to achieve attitude adjustment and control the extension and rotation of the turbofan 3. The wing assembly 11 relies on torsion springs for adaptive passive deployment. Neither of them requires additional independent drive sources. They share the same base structure such as the mounting frame 2, and the components are highly integrated and interchangeable, reducing redundant transmission components, lowering the overall weight and flight energy consumption, extending the endurance, and reducing the number of electrical control points and sources of failure, thus improving the operational reliability in complex environments.

[0080] Small, rectangular-nest-shaped aircraft prioritize portability and flexibility. Their compact fuselage and small stowage size, coupled with their lack of heavy-load capacity, make them ideal for light-duty operations. This allows for the use of spring-loaded extension components with prismatic, quincunx, slotted, and toothed adjustment rods paired with retractable wings. During flight or extension, the springs slide synchronously with the extension rods. In this process, the springs not only bear axial loads but also dynamic impacts such as airflow disturbances and fuselage vibrations. These dynamic forces cause repeated elastic deformation of the springs, accelerating elastic fatigue. Furthermore, the force fluctuations during sliding further reduce load transmission stability, making it difficult for the springs to bear loads stably. This dynamic loss is particularly pronounced under heavy-load conditions, ultimately affecting the overall load-bearing capacity.

[0081] Medium-sized prismatic aircraft need to balance portability and a certain load-bearing capacity for medium-distance, medium-intensity operations. With a moderate fuselage size, it can be adapted to a variety of complex scenarios. Corresponding to the combination scheme of spring-tensioned extension components 12-prism, plum blossom, and rod groove type extension rod 1203, telescopic rod type extension components 8-column type inner push rod, plum blossom type inner push rod and telescopic wing.

[0082] Large-scale spherical aircraft require heavy-load, long-distance, and high-precision operations. Due to their large fuselage size and high load-bearing capacity, the combination of the worm-type extension assembly 9, the telescopic rod extension assembly 8, the cylindrical external push tube 805, the prismatic internal push rod 802, and the telescopic wing is the only combination that can meet the heavy-load requirements of large-scale aircraft.

[0083] The wing assembly 11 can be flexibly combined with four types of extended components and all sub-structures. Combined with the two forms of adjacent / diagonal arrangement of the connecting rods 10, it can realize "complete aircraft - simple aircraft". It can also switch between multiple forms by selecting "light - medium - heavy" according to the load, or "portable emergency - complex terrain - high precision heavy load" according to the environment. Without replacing the whole machine, it can be adapted to various scenarios such as emergency rescue, inspection, plant protection, surveying and mapping, and heavy load delivery by simply selecting the extended components and adjusting the wing deployment state. At the same time, the wing occupies little space when stored and has sufficient lift when deployed, maximizing the aerodynamic performance of the flight while ensuring the convenience of the square nest storage.

[0084] With excellent adaptability and expandability, this invention balances practicality and innovation. The telescopic structure design of the wing assembly 11 can adapt to all types of extension components, whether it is the lightweight and convenient spring compression or spring extension type, or the high-precision control of the worm gear type or the heavy-duty adaptation of the telescopic rod type, all can achieve perfect connection. The wing assembly 11 can flexibly choose automatic passive deployment or torsion motor driven deployment according to the size and load requirements of the aircraft. The arrangement of the connecting rods 10 can be switched, further improving the versatility and expandability of the equipment, adapting to the usage requirements of different specifications of square nest aircraft, highlighting the innovation and practicality of this invention.

[0085] This invention features a highly adaptable and flexible structure, suitable for nest storage and diverse usage needs. The overall layout is compact, and the integrated design of connecting rod 10, auxiliary frame 6, and mounting frame 2 meets the storage requirements of the nest aircraft. It also provides various types of extension components and subdivided structures, including spring compression, spring extension, worm gear, and telescopic rod types, which can be flexibly selected according to the aircraft model and working conditions. Furthermore, the connecting rod 10 can be arranged adjacently or diagonally to adapt to complete or simple aircraft structures, demonstrating excellent versatility and expandability.

[0086] The telescopic and rotation linkage is integrated, which simplifies the structure and ensures reliable operation. There is no need to add an additional rotation drive mechanism. By adjusting the guide hole 602, the spiral groove and the guide column, the telescopic component can be extended and retracted while driving the turbofan 3 to rotate synchronously. This simplifies the overall structure, reduces weight and energy consumption, and ensures smooth operation without deviation through multiple limit and guide designs, thereby improving the flight stability of the aircraft and the service life of the equipment.

[0087] It should be stated that the above-described specific embodiments are merely preferred embodiments of the present invention and the technical principles employed. Those skilled in the art should understand that various modifications, equivalent substitutions, and variations can be made to the present invention. However, such variations, as long as they do not depart from the spirit of the present invention, should be within the scope of protection of the present invention. Furthermore, some terminology used in this specification and claims is not limiting, but merely for ease of description.

Claims

1. An automatic deployment structure for a square-nest aircraft, characterized in that: The system includes multiple parallel connecting rods (10), with auxiliary frames (6) fixedly installed at both ends of each connecting rod (10). One end of the corner of each auxiliary frame (6) is connected to a mounting frame (2). Both sides of the mounting frame (2) are provided with stretching components that can extend along the length direction. The end of each stretching component is equipped with a tilting motor (4) through a mounting housing. The drive end of the tilting motor (4) is connected to a turbofan (3). The corner of the auxiliary frame (6) includes a connecting hole (601) adapted to the connecting rod (10) and an adjustment guide hole (602) adapted to the telescopic end of the stretching component. The adjustment guide hole (602) is located adjacent to or diagonally opposite to the connecting hole (601). When the stretching component slides along the length direction of the mounting frame (2), the turbofan (3) rotates along the axis of the stretching component.

2. The automatic deployment structure for a square-nest aircraft according to claim 1, characterized in that: The stretching component includes a spring compression stretching component (7). The mounting frame (2) has mounting pipes (201) at both ends. The mounting pipes (201) have spring slots (203) at both ends. The position of the mounting pipes (201) corresponds to the position of the adjustment guide hole (602). The spring compression stretching component (7) is slidably installed on the inner side of the mounting pipes (201). The spring compression stretching component (7) includes a compression spring (710). The compression spring (710) is hung and connected to the spring slots (203).

3. The automatic deployment structure for a square-nest aircraft according to claim 1, characterized in that: The stretching assembly includes a worm-type stretching assembly (9), which is an internal spiral worm structure or an external spiral worm structure. The two ends of the mounting frame (2) are provided with mounting pipes (201), and the two ends of the mounting pipes (201) are provided with turbine slots (204). The worm-type stretching assembly (9) includes an adjusting worm (901). The end face of the mounting frame (2) is fixedly mounted with a transmission turbine (903) with a servo motor. The transmission turbine (903) meshes with the adjusting worm (901) through the turbine slots (204). The internal spiral worm gear structure includes an internal spiral groove (202) opened inside the installation pipe (201), and a guide post four (902) that slides along the internal spiral groove (202) is fixedly connected to the outer side of the adjusting worm gear (901). The external helical worm gear structure includes an external helical groove (904) opened on the outside of the adjusting worm (901), and the auxiliary frame (6) is provided with an adjusting guide hole (602) adapted to the cross section of the adjusting worm (901).

4. The automatic deployment structure for a square-nest aircraft according to claim 1, characterized in that: The stretching component includes a telescopic rod stretching component (8). The mounting frame (2) has mounting slots (206) on both sides. The fixed end of the telescopic rod stretching component (8) is installed inside the mounting slot (206). The telescopic end of the telescopic rod stretching component (8) is slidably connected to the adjustment guide hole (602).

5. The automatic deployment structure for a square-nest aircraft according to claim 1, characterized in that: The stretching component includes a spring-tension stretching component (12). The two ends of the mounting frame (2) are provided with mounting pipes (201). A tension spring (1201) is installed on the inner side of the mounting pipe (201). The spring-tension stretching component (12) includes stretching rods with different cross sections. The two ends of the tension spring (1201) are respectively engaged with the stretching rods. The stretching rods include a prismatic stretching rod (1202) with an overall spiral shape, a plum blossom-shaped stretching rod (1204), and a rod groove-shaped stretching rod (1203) with a spiral groove on the rod body. The auxiliary frame (6) is provided with an adjustment guide hole (602) that matches the cross section of the stretching rod.

6. The automatic deployment structure for a square-nest aircraft according to claim 2, characterized in that: The spring compression extension assembly (7) includes various adjusting rods with different cross sections. One end of the compression spring (710) is fixedly connected to the adjusting rod. The adjusting rod includes a grooved adjusting rod (701), a plum blossom-shaped adjusting rod (702), and a prism-shaped adjusting rod (703). The plum blossom-shaped adjusting rod (702) and the prism-shaped adjusting rod (703) are spiral-shaped. The outer side of the grooved adjusting rod (701) is provided with an outer spiral groove (7011). The auxiliary frame (6) is provided with an adjusting guide hole (602) that matches the cross section of the adjusting rod. When the adjusting rod is a grooved adjusting rod (701), a guide post (7012) extending to the inner side of the outer spiral groove (7011) is installed on the inner side of the adjusting guide hole (602).

7. The automatic deployment structure for a square-nest aircraft according to claim 6, characterized in that: The adjusting rod also includes a toothed adjusting rod (704), and an inner spiral groove (202) is provided on the inner side of the installation pipe (201). A guide post (7041) that can slide along the inner spiral groove (202) is fixedly installed at the end of the toothed adjusting rod (704).

8. The automatic deployment structure for a square-nest aircraft according to claim 4, characterized in that: The inner side of the mounting slot (206) is fitted with a telescopic outer tube (801). The end face of the mounting slot (206) is provided with a limit block (205). The inner side of the telescopic outer tube (801) is slidably connected with a variety of inner push rods with different cross sections. The inner push rods include a rhomboid inner push rod (802), a plum blossom-shaped inner push rod (803), and a circular inner push rod (804). The auxiliary frame (6) is provided with an adjustment guide hole (602) that matches the cross section of the inner push rod. The end face of the inner push rod is connected to a tilting motor (4).

9. The automatic deployment structure for a square-nest aircraft according to claim 1, characterized in that: The mounting frame (2) is provided with mounting pipes (201) at both ends. The inner side of the mounting pipe (201) is provided with an inner spiral groove (202). The telescopic rod type extension component (8) also includes a cylindrical outer push tube (805) and a cylindrical inner push rod (806). The cylindrical inner push rod (806) is fixedly installed on the inner side of the mounting pipe (201). The outer side of the cylindrical outer push tube (805) is provided with a guide post three (807) that can slide along the inner spiral groove (202).

10. The automatic deployment structure for a square-nest aircraft according to claim 1, characterized in that: A frame (1) is mounted on the outside of the mounting frame (2), a fairing (5) is mounted on the end face of the auxiliary frame (6), and a wing assembly (11) is mounted on the outside of the frame (1). The wing assembly (11) includes a side wing body (1110). The mounting frame (2) has a guide groove (1101), and oblique grooves (1102) are provided on both sides of the guide groove (1101). A guide shaft (1106) is provided in the guide groove (1101), and a guide connecting shaft (1105) is slidably provided inside the guide groove (1101). The wing body (1110) and the guide connecting shaft (1105) are hinged together. The top of the wing body (1110) is provided with a wing connecting shaft (1103) that slides along the oblique through groove (1102). The guide connecting shaft (1105) and the two wing connecting shafts (1103) are connected by a torsion spring (1104). The connecting rod (10) is hinged to the tail wing motor (1108) and the torsion spring (1109). The driving end of the tail wing motor (1108) is connected to the tail wing body (1107). The two ends of the torsion spring (1109) are respectively connected to the tail wing motors (1108) on both sides. When the side wing body (1110) is in the retracted state, the wing connecting shaft (1103) is near the far end of the oblique through groove (1102), and the torsion spring (1104) is in a torsion state; when the side wing body (1110) is in the deployed state, the wing connecting shaft (1103) is near the near end of the oblique through groove (1102), and the torsion spring (1104) is in a non-stressed state.

Images