Modeled unmanned aerial vehicle capable of switching between manned mode and unmanned mode of wire transmission control aircraft

Abstract

The invention relates to the technical field of aircraft design, in particular to a wired control aircraft modeling unmanned aerial vehicle capable of switching between a manned mode and an unmanned mode. According to the technical scheme, the aircraft comprises an aircraft shell, a replaceable front cabin door, a replaceable rear cabin door and a replaceable lower cabin door. The core is that a wire transmission control system is integrated in a front cabin door which can be opened upwards to form a modularized functional unit. A front door installation table and a wire transmission operation table are arranged on the inner side of the front cabin door, are electrically connected through a plug and a connector on the top and are quickly and mechanically locked and released through an installation mechanism. A sliding rail and a sliding block are arranged in the aircraft shell and used for flexibly positioning the wire transmission operation table and the driver seat. The front cabin door and the rear cabin door are synchronously driven to open and close by a single motor matched with a transmission mechanism. Through modularized replacement of the front cabin door, rapid and safe switching between a manned mode and an unmanned mode is achieved, the problems that a traditional airplane is single in mode and high in refitting cost are solved, and using flexibility and safety are improved.

Description

Technical Field

[0001] This invention relates to the field of aircraft design technology, and in particular to a modular unmanned aerial vehicle (UAV) with fly-by-wire control that allows for manned / unmanned operation. Background Technology

[0002] In modern aviation operations, mission requirements are becoming increasingly diverse and dynamic, placing higher demands on the versatility of aircraft. The same flight platform may need to alternate between complex missions requiring direct pilot control and standardized missions that can be executed autonomously within a single mission or different mission cycles. This mixed mission scenario urgently requires aircraft to have the ability to flexibly and efficiently switch between manned and unmanned modes in order to maximize platform utilization and adapt to complex application environments.

[0003] Currently, manned and unmanned aircraft in the aviation field mostly follow independent design concepts and development paths. They typically have dedicated airframe structures, cockpit layouts, and flight control systems. When mission requirements shift from one mode to another, the common practice is to utilize specially built aircraft or physically modify existing aircraft. Modifications usually involve substantial alterations and reintegration of cockpit control equipment, cabling, and control software, a complex process that relies on specific expertise.

[0004] However, existing technologies based on independent design systems and substantial modifications have resulted in the functionalities of single aircraft models being fixed, and their operating modes lacking the necessary flexibility. This makes it difficult for existing aircraft to respond quickly and economically to ever-changing mixed mission requirements, resulting in problems such as poor aircraft versatility, insufficient mission adaptability, and high costs and timelines associated with cross-mode modifications. Summary of the Invention

[0005] This invention provides the following technical solution: A modular unmanned aerial vehicle (UAV) with fly-by-wire control, capable of switching between manned and unmanned operation, includes an aircraft shell and also comprises: A replaceable front cabin door is located at the front of the aircraft fuselage, a rear cabin door is located at the rear, and a lower cabin door is installed at the bottom of the rear. The aircraft shell and the lower cabin door are connected by an electric push rod. A drive mechanism is provided between the front cabin door, the aircraft shell and the rear cabin door. A front door mounting platform is installed inside the front cabin door. A wire transmission operating platform is attached to one side of the outer wall of the front door mounting platform. A plug is provided on the top of the wire transmission operating platform and is connected to the connector on the top of the front door mounting platform. The wire transmission operating platform and the front door mounting platform are connected by an installation mechanism. A slide rail is installed inside the aircraft shell, and a lockable slider slides on the outer wall of the slide rail. The wired control panel and the pilot's seat can be installed on the upper surface of the slider.

[0006] By adopting the above technical solution, the system function can be reconfigured through a replaceable front cabin door. When a functional front cabin door is installed, the aircraft enters manned mode; when replaced with a regular front cabin door, it reverts to unmanned mode. The cooperation of rails and sliders allows the pilot unit to move longitudinally within the cabin, enabling flexible adjustment of the pilot position. Modular design significantly improves the aircraft's adaptability to different missions; enables rapid switching between manned and unmanned modes, greatly shortening mode transition time; and improves cabin space utilization, allowing for optimization of the cabin layout according to mission requirements.

[0007] Optionally, the drive mechanism is mounted on the inner wall of the aircraft shell via a mounting plate. A motor is mounted on one side of the outer wall of the mounting plate, and a rotating shaft is connected to the middle of the motor via a bearing. A drive wheel is mounted on the output end of the motor and meshes with a driven wheel on the outer wall of the rotating shaft.

[0008] By adopting the above technical solution, the initial torque is provided by the motor, and power transmission and speed conversion are achieved through gear meshing between the driving and driven wheels. The mounting plate ensures the stable installation of the drive components. It provides reliable power output, ensuring the stability of the door drive; the gear transmission achieves effective power distribution; and it simplifies the structure of the drive system and improves the ease of system maintenance.

[0009] Optionally, universal joints are installed at both ends of the rotating shaft, and a cross shaft is provided inside the universal joint. Another universal joint is connected to one side of the outer wall of the cross shaft, and a threaded column is installed on its outer wall. A threaded sleeve that matches the thread of the outer wall of the threaded column is threadedly connected to the outer wall of the threaded column.

[0010] By adopting the above technical solution, power is synchronously transmitted to both sides via a rotating shaft, universal joints and cross shafts compensate for installation errors, and threaded columns and threaded sleeves convert rotational motion into linear motion. This ensures the synchronous movement of the front and rear hatches, improving the coordination of hatch actions; the universal joint design adapts to changes in the hatch movement angle; and precise position control is achieved using screw pairs.

[0011] Optionally, the end of the threaded sleeve is connected to the front and rear hatches via an adapter shaft.

[0012] By adopting the above technical solution, the linear thrust of the threaded sleeve is directly applied to the front and rear hatches via an adapter shaft. This achieves efficient power transmission, ensuring smooth opening and closing of the hatches; provides reliable connection support, ensuring long-term stability; and optimizes the force transmission path, improving the efficiency of the entire drive system.

[0013] Optionally, the installation mechanism is installed at both ends of the top of the front door mounting platform via a fixed base. The fixed base is rotatably provided with a rotating shaft, and the outer wall of the rotating shaft has a locking block. The inside of the wire transmission operating platform is provided with a slot corresponding to the locking block.

[0014] By adopting the above technical solution, a mounting base is provided by a fixed seat, and a rotating shaft provides the rotation center for the locking block. The engagement of the locking block and the slot enables rapid locking. This allows for the rapid installation and disassembly of the wire-driven operating console, significantly improving operational efficiency; mechanical interlocking ensures the reliability of the connection; and the installation process is simplified, reducing operational difficulty.

[0015] Optionally, a rotating ring is fixed to the inner wall of the card block, and torsion springs are sleeved on both sides of the outer wall of the rotating shaft.

[0016] By adopting the above technical solution, a rotating ring connects the locking block and the torsion spring, utilizing the elastic potential energy of the torsion spring to drive the locking block to automatically return to its original position. This provides the driving force for automatic locking, ensuring timely locking; the spring energy storage and release mechanism achieves rapid response; and it enhances the reliability of locking, preventing accidental loosening.

[0017] Optionally, one end of the torsion spring is fixed to the outer wall of the rotating ring, and the other end is fixed to the inside of the fixed base.

[0018] By adopting the above technical solution, and fixing both ends of the torsion spring to the rotating ring and the fixed base respectively, an effective torque transmission is achieved. This ensures the effective utilization of the spring force, improves the stability of the locking force, optimizes the force transmission efficiency, reduces energy loss, enhances the system's durability, and extends its service life.

[0019] Optionally, a threaded shaft is rotatably provided on the top of the fixed base, a handle is fixed to one end of the threaded shaft, and a limiting plate that matches the thread of the outer wall of the threaded shaft is provided on its outer wall.

[0020] By adopting the above technical solution, the rotating handle drives the threaded shaft, which in turn pushes the limit plate to achieve secondary locking, providing additional safety protection and effectively preventing accidental unlocking caused by vibration; precise position control is achieved through threaded transmission; and the overall connection reliability is enhanced, ensuring flight safety.

[0021] Optionally, the limiting plate is attached to one side of the outer wall of the card block, and the other side of the outer wall of the card block slides inside the front door mounting platform and the wire transmission operating platform.

[0022] By adopting the above technical solution, the rotating handle drives the threaded shaft, which in turn pushes the limit plate to achieve secondary locking, providing additional safety protection and effectively preventing accidental unlocking caused by vibration; precise position control is achieved through threaded transmission; and the overall connection reliability is enhanced, ensuring flight safety.

[0023] Optionally, the aircraft's outer shell is provided with wiring that runs through the interior of the front cabin door and connects to the front door mounting platform.

[0024] By adopting the above technical solution, signal transmission between the front door mounting station and the aircraft's main control system is achieved through wiring. This ensures stable transmission of control signals, improves system reliability, avoids complex wiring work through pre-set wiring, and provides a complete signal path, guaranteeing the real-time performance of flight control.

[0025] In summary, the present invention has at least one of the following beneficial technical effects: This invention enables rapid and low-cost switching between manned and unmanned modes of the aircraft through the modular design of the front cabin door, greatly improving the aircraft's versatility and mission adaptability, and significantly reducing the modification and maintenance costs caused by mode switching.

[0026] Furthermore, the use of upper flexible connection and quick-connect interface avoids the wear and poor contact problems caused by frequent plugging and unplugging of traditional cables. At the same time, the use of mechanical interlock mechanism ensures the connection reliability of the wire transmission control panel in vibration environment, resulting in high overall safety. Attached Figure Description

[0027] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0028] Figure 1 This is a schematic diagram of the overall structure of the UAV provided in an embodiment of the present invention; Figure 2 This is a schematic diagram of the outer casing provided in an embodiment of the present invention; Figure 3 This is a schematic diagram of the drive mechanism structure provided in an embodiment of the present invention; Figure 4 This is a schematic diagram of the mounting platform structure provided in an embodiment of the present invention; Figure 5 This is a schematic diagram of the operating console structure provided in an embodiment of the present invention; Figure 6 This is a schematic diagram of the installation mechanism provided in an embodiment of the present invention.

[0029] Explanation of reference numerals in the attached figures: 1. Aircraft shell; 2. Front cabin door; 3. Rear cabin door; 4. Lower cabin door; 5. Mounting plate; 6. Motor; 7. Drive wheel; 8. Driven wheel; 9. Rotating shaft; 10. Universal joint; 11. Cross shaft; 12. Threaded post; 13. Threaded sleeve; 14. Adapter shaft; 15. Electric push rod; 16. Wiring; 17. Front door mounting platform; 18. Connector; 19. Wired control panel; 20. Plug; 21. Slide rail; 22. Slider; 23. Mounting base; 24. Rotating shaft; 25. Locking block; 26. Rotating ring; 27. Torsion spring; 28. Threaded shaft; 29. ​​Handle; 30. Limit plate. Detailed Implementation

[0030] 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.

[0031] The terms "first," "second," etc., used in the specification, claims, and accompanying drawings of this invention are used to distinguish different objects, not to describe a specific order. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or apparatus that includes a series of steps or units is not limited to the listed steps or units, but may optionally include steps or units not listed, or may optionally include other steps or units inherent to these processes, methods, products, or apparatuses.

[0032] In this document, references to "embodiment" or "implementation" mean that a particular feature, structure, or characteristic described in connection with an embodiment or implementation may be included in at least one embodiment of the invention. The appearance of this phrase in various places throughout the specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment mutually exclusive with other embodiments. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described herein can be combined with other embodiments.

[0033] In modern aviation operations, mission requirements are becoming increasingly diverse and dynamic, placing higher demands on the versatility of aircraft. The same flight platform may need to alternate between complex missions requiring direct pilot control and standardized missions that can be executed autonomously within a single mission or different mission cycles. This mixed mission scenario urgently requires aircraft to have the ability to flexibly and efficiently switch between manned and unmanned modes in order to maximize platform utilization and adapt to complex application environments.

[0034] Currently, manned and unmanned aircraft in the aviation field mostly follow independent design concepts and development paths. They typically have dedicated airframe structures, cockpit layouts, and flight control systems. When mission requirements shift from one mode to another, the common practice is to utilize specially built aircraft or physically modify existing aircraft. Modifications usually involve substantial alterations and reintegration of cockpit control equipment, cabling, and control software, a complex process that relies on specific expertise.

[0035] However, existing technologies based on independent design systems and substantial modifications have resulted in the functionalities of single aircraft models being fixed, and their operating modes lacking the necessary flexibility. This makes it difficult for existing aircraft to respond quickly and economically to ever-changing mixed mission requirements, resulting in problems such as poor aircraft versatility, insufficient mission adaptability, and high costs and timelines associated with cross-mode modifications.

[0036] Please see Figure 1 and Figure 2 This invention proposes a modular unmanned aerial vehicle (UAV) with a fly-by-wire control system that allows for manned / unmanned operation. The system includes the main body and a platform, an aircraft shell 1 providing the mounting foundation and structural support for all other components, and a replaceable front door 2 located at the front of the shell 1. The front door 2 has two forms (functional / standard) that directly determine the aircraft's operating mode. In manned mode, it integrates the entire pilot control interface, with a rear door 3 at the rear. The rear door 3 and the front door 2 work together to form a continuous cabin space, facilitating cargo loading and unloading and personnel emergency evacuation. A lower door 4 is installed at the rear bottom. In one implementation, the aircraft shell 1 and the lower door 4 are connected by an electric push rod 15. The lower door 4 provides access to the cabin from the bottom of the aircraft, forming a three-dimensional, multi-directional cargo storage and operation system together with the front door 2 and the rear door 3. A drive mechanism is provided between the front door 2, the aircraft shell 1, and the rear door 3. A front door mounting platform 17 is installed inside the front door 2 and fixed to it. The structural base on the front door mounting platform 17 is mainly used to support the fly-by-wire control console 19 and provide an electrical interface. The fly-by-wire control console 19 is attached to one side of the outer wall of the front door mounting platform 17. The fly-by-wire control console 19 is the "command center" in manned mode, integrating joysticks, displays and controllers. It is the core interface for pilot-aircraft interaction. The fly-by-wire control console 19 is equipped with a plug 20 on its top and is connected to the connector 18 on the top of the front door mounting platform 17. The fly-by-wire control console 19 and the front door mounting platform 17 are connected by an installation mechanism. The connector 18 and the plug 20 together form an automatically docking electrical connector. When the cabin door is closed, the connection is automatically completed, realizing plug-and-play and avoiding tedious manual wiring. The slide rail 21 is installed inside the aircraft shell 1. A lockable slider 22 slides on the outer wall of the slide rail 21. The wired control panel 19 and the pilot seat can be installed on the upper surface of the slider 22. The slide rail 21 provides precise guidance for the slider 22, ensuring that the pilot unit (control panel or seat) can move linearly along a predetermined path. The aircraft's outer shell 1 contains a wiring 16 that runs through the interior of the forward cabin door 2 and connects to the forward door mounting platform 17. The following is a detailed description of the fly-by-wire control aircraft: In this embodiment, the entire manned control system, including the fly-by-wire console 19, is integrated into the interior of the replaceable front cabin door 2. When the front cabin door 2 is closed, the plug 20 on the fly-by-wire console 19 automatically connects with the connector 18 on the front door mounting platform 17, allowing control signals to be connected to the aircraft's flight control backbone network via line 16. When switching to unmanned mode, simply replace the entire front cabin door 2 with the integrated control system with a regular unmanned front cabin door 2. In manned mode, the fly-by-wire console 19 or the pilot's seat can be mounted on a slider 22, which can move along a rail 21 fixed inside the aircraft shell 1. This allows for flexible adjustment of the pilot's seat position within the cabin according to different mission requirements or pilot habits. Furthermore, the front cabin door 2 and the rear cabin door 3 can open simultaneously, forming a through-type layout. This facilitates rapid loading and unloading of cargo in unmanned cargo mode and also enables rapid two-way evacuation of passengers in manned passenger mode.

[0037] like Figures 1-3 As shown, the fly-by-wire controlled aircraft also includes a drive mechanism located between the front cabin door 2, the aircraft shell 1, and the rear cabin door 3. In one embodiment, the drive mechanism is mounted on the inner wall of the aircraft shell 1 via a mounting plate 5. A motor 6 is mounted on one side of the outer wall of the mounting plate 5. The motor 6 serves as the power source for the cabin door drive, providing the initial torque for the entire opening and closing action. A rotating shaft 9 is connected to the middle of the motor 6 via a bearing. The rotating shaft 9 is a transmission shaft that runs laterally through the fuselage and is responsible for synchronously distributing power to both sides of the fuselage. A drive wheel 7 is mounted on the output end of the motor 6 and meshes with a driven wheel 8 on the outer wall of the rotating shaft 9. The drive wheel 7 and the driven wheel 8 form a first-stage reduction and torque amplification mechanism, which transmits the power of the motor 6 to the rotating shaft 9. Universal joints 10 are installed at both ends of the rotating shaft 9, and a cross shaft 11 is set inside the universal joint 10. Another universal joint 10 is connected to one side of the outer wall of the cross shaft 11. The universal joint 10 and the cross shaft 11 are key coupling components used to compensate for the misalignment of the axis caused by the rotation of the hatch and manufacturing errors, and to ensure smooth power transmission. A threaded column 12 is installed on its outer wall. A threaded sleeve 13 that matches the thread of the outer wall of the threaded column 12 is threadedly connected to the threaded column 12. The threaded column 12 and the threaded sleeve 13 form a helical pair, which accurately converts the rotational motion transmitted from the rotating shaft 9 into linear motion, thereby pushing and pulling the hatch. The end of the threaded sleeve 13 is connected to the front hatch 2 and the rear hatch 3 through the adapter shaft 14. The adapter shaft 14 is the last stage of the power output linkage, which directly applies the linear thrust generated by the threaded sleeve 13 to the hatch. The drive mechanism is described in detail below: In this embodiment, the motor 6 operates, driving the drive wheel 7 at its output end to rotate. The drive wheel 7, through meshing with the driven wheel 8, transmits power to the horizontally positioned rotating shaft 9. Both ends of the rotating shaft 9 are connected by universal joints 10. The cross shaft 11 structure inside the universal joint 10 ensures that power can be transmitted in different directions, thereby compensating for installation errors and adapting to angle changes during hatch opening and closing. Power is transmitted through the universal joint 10 to the threaded column 12, driving the precisely fitted threaded sleeve 13 to produce axial linear motion. Finally, the linear thrust at the end of the threaded sleeve 13 acts on the front hatch 2 and the rear hatch 3 respectively through the adapter shaft 14, realizing the synchronous and smooth opening and closing of the two hatches.

[0038] like Figures 1-6 As shown, the fly-by-wire aircraft also includes an installation mechanism that connects the fly-by-wire control console 19 and the front door mounting platform 17. In one embodiment, the installation mechanism is installed on both ends of the top of the front door mounting platform 17 via a fixed seat 23. The fixed seat 23 is installed on the front door mounting platform 17 and serves as the base of the quick-installation mechanism, used to accommodate and support the locking components. The fixed seat 23 is rotatably provided with a rotating shaft 24, which provides a rotation center for the locking block 25. The locking block 25 is rotatably mounted on the outer wall of the rotating shaft 24. The locking block 25 is the core actuator of the locking mechanism. Through its "locking in" and "unlocking out" actions, the fly-by-wire control console 19 is mechanically locked and released. The fly-by-wire control console 19 has a slot inside that corresponds to the locking block 25. A rotating ring 26 is fixed to the inner wall of the locking block 25. The rotating ring 26 is the intermediate component connecting the locking block 25 and the torsion spring 27, used to transmit the spring force. Torsion springs 27 are sleeved on both sides of the outer wall of the rotating shaft 24. The torsion springs 27 provide the driving force for automatic locking. When the locking block 25 is pushed in, it stores energy and automatically releases energy to drive the locking block 25 to reset and lock. One end of the torsion spring 27 is fixed to the outer wall of the rotating ring 26, and the other end is fixed to the inside of the fixing base 23. A threaded shaft 28 is rotatably mounted on the top of the fixed base 23. The threaded shaft 28 serves as a drive screw for the second locking mechanism, and its rotational motion can be converted into the linear motion of the limiting plate 30. A handle 29 is fixed to one end of the threaded shaft 28, providing the operator with a labor-saving and convenient grip point for manually rotating the threaded shaft 28. The outer wall of the handle 28 is provided with a limiting plate 30 that matches the thread on the outer wall of the threaded shaft 28. The limiting plate 30 is the final actuator for the second safety locking mechanism. Its forward movement can block the locking block 25, preventing it from accidentally disengaging during vibration, which greatly improves the reliability of the connection. The limiting plate 30 fits against one side of the outer wall of the locking block 25, and the other side of the outer wall of the locking block 25 slides inside the front door mounting platform 17 and the wire transmission operating platform 19. The installation mechanism is described in detail below: In this embodiment, during installation, the wire transmission operating platform 19 is first installed above the slider 22. Then, guided by the slider 22 and the slide rail 21, the wire transmission operating platform 19 is precisely positioned, aligning the slot on the wire transmission operating platform 19 with the locking block 25 on the fixed base 23. During the pushing process, the locking block 25 is compressed and rotates around the rotating shaft 24, pressing the rotating ring 26 inside, causing the torsion spring 27 sleeved on the rotating shaft 24 to accumulate elastic potential energy. When the wire transmission operating platform 19 reaches the predetermined position, the locking block 25 quickly rebounds under the restoring force of the torsion spring 27, locking into the slot and completing the initial mechanical locking. To ensure absolute reliability of the lock, the handle 29 is then rotated, causing the threaded shaft 28 fixed thereto to screw in, pushing the limiting plate 30 at its front end forward until it fits tightly against the outside of the locking block 25. This effectively prevents the locking block 25 from accidentally coming off under the action of external forces such as vibration, thereby enabling the quick and safe disassembly and assembly of the wire-driven operating console 19. Finally, the slider 22 is removed, and the driver's seat is installed on the slider 22, which is convenient to use in conjunction with the slide rail 21.

[0039] Specifically, when the aircraft needs to switch from unmanned mode to manned mode, the operator first installs the functional front cabin door 2 with integrated wired control console 19 at the designated position at the front of the aircraft shell 1. During the closing of the front cabin door 2, the front door mounting platform 17 installed inside the front cabin door 2 moves synchronously with the door body, so that the electrical connector 18 on its top automatically aligns with the plug 20 at the top of the wired control console 19 and achieves a reliable connection, so that the pilot's control commands can be transmitted to the aircraft's main flight control system through the shielded line 16, establishing a complete signal path.

[0040] After completing the electrical system connection, the mechanical system installation and positioning begins. The operator places the wire-driven control panel 19 on the movable slider 22 and pushes it along two parallel slide rails 21 fixed inside the aircraft shell 1 to the preset working position. During this process, the trapezoidal slot on the side of the wire-driven control panel 19 contacts the locking block 25 in the fixed seat 23 installed on the front door mounting platform 17, pushing the locking block 25 to rotate around the rotating shaft 24. This rotation is transmitted through the rotating ring 26 fixed to the inner wall of the locking block 25, causing the two torsion springs 27 sleeved on the rotating shaft 24 to elastically deform and store mechanical potential energy. When the wire-driven control panel 19 reaches the predetermined installation position, the locking block 25 quickly rebounds under the restoring torque of the torsion springs 27, accurately locking into the slot of the wire-driven control panel 19, completing the first stage of mechanical locking.

[0041] To ensure the reliability of the connection in a vibration environment, the operator then rotates the handle 29 mounted on the top of the fixed base 23, which drives the threaded shaft 28 connected to it to rotate. The rotation of the threaded shaft 28 drives the limiting plate 30 at its front end to move forward along the axis until it fits tightly against the outer surface of the locking block 25, forming a second mechanical protection, which effectively prevents accidental loosening caused by vibration during flight.

[0042] Regarding the cabin door control system, when the cabin door needs to be opened or closed, the motor 6 mounted on the mounting plate 5 starts, driving the drive wheel 7 on its output shaft to rotate. The drive wheel 7 transmits power to the transversely mounted rotating shaft 9 through gear meshing with the driven wheel 8. The two ends of the rotating shaft 9 are connected by universal joints 10, and the cross shaft 11 structure inside the universal joint 10 ensures that the power can be transmitted at a certain angle. The power is finally transmitted to the threaded column 12, which converts the rotational motion into the linear motion of the threaded sleeve 13 through the threaded pair. The threaded sleeve 13 is connected to the front cabin door 2 and the rear cabin door 3 through the adapter shaft 14, thereby realizing the synchronous and coordinated movement of the front cabin door 2 and the rear cabin door 3. At the same time, the lower cabin door 4 at the bottom of the aircraft moves in coordination under the drive of the electric push rod 15, forming a complete through-type working passage with the front cabin door 2 and the rear cabin door 3.

[0043] When switching from manned to unmanned mode, first rotate handle 29 in the opposite direction to move limit plate 30 backward, releasing the constraint on latch 25. Then pull the wired control panel 19 outward, causing latch 25 to rotate out of the slot against the force of torsion spring 27. Finally, remove the entire functional front door 2 and replace it with a standard front door 2, thus completing the entire mode conversion process.

[0044] In this invention, the terms "embodiment" and "implementation" mean that a specific feature, structure, or characteristic described in connection with an embodiment can be included in at least one embodiment of the invention. The appearance of these phrases in various places in the specification does not necessarily refer to the same embodiment, nor are they independent or alternative embodiments mutually exclusive with other embodiments. Those skilled in the art will understand, explicitly and implicitly, that the embodiments described in this invention can be combined with other embodiments. Furthermore, it should be understood that the features, structures, or characteristics described in the various embodiments of this invention can be arbitrarily combined to form yet another embodiment that does not depart from the spirit and scope of the technical solution of this invention, provided there is no contradiction between them.

[0045] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to the above preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions to the technical solutions of the present invention should not depart from the spirit and scope of the technical solutions of the present invention.

Claims

1. A modular unmanned aerial vehicle (UAV) with wire-driven control that allows for manned / unmanned operation, comprising an aircraft shell (1), characterized in that, Also includes: A replaceable front cabin door (2) is provided at the front of the aircraft shell (1), a rear cabin door (3) is provided at the rear, and a lower cabin door (4) is installed at the bottom of the rear. The aircraft shell (1) and the lower cabin door (4) are connected by an electric push rod (15). A drive mechanism is provided between the front cabin door (2), the aircraft shell (1) and the rear cabin door (3). A front door mounting platform (17) is installed inside the front cabin door (2). A wire transmission operating platform (19) is attached to one side of the outer wall of the front door mounting platform (17). A plug (20) is provided on the top of the wire transmission operating platform (19) and is connected to the connector (18) on the top of the front door mounting platform (17). The wire transmission operating platform (19) and the front door mounting platform (17) are connected by an installation mechanism. A slide rail (21) is installed inside the aircraft shell (1), and a lockable slider (22) slides on the outer wall of the slide rail (21). The wire-driven control panel (19) and the pilot seat can be installed on the upper surface of the slider (22).

2. The modular unmanned aerial vehicle (UAV) with manned / unmanned operation as described in claim 1, characterized in that, The drive mechanism is mounted on the inner wall of the aircraft shell (1) via a mounting plate (5). A motor (6) is mounted on one side of the outer wall of the mounting plate (5), and a rotating shaft (9) is connected to the middle of the plate via a bearing. A drive wheel (7) is mounted on the output end of the motor (6) and meshes with a driven wheel (8) on the outer wall of the rotating shaft (9).

3. The modular unmanned aerial vehicle (UAV) with manned / unmanned operation as described in claim 2, characterized in that, Universal joints (10) are installed at both ends of the rotating shaft (9), and a cross shaft (11) is provided inside the universal joint (10). Another universal joint (10) is connected to one side of the outer wall of the cross shaft (11), and a threaded column (12) is installed on its outer wall. A threaded sleeve (13) that matches the threaded thread on the outer wall of the threaded column (12) is threadedly connected to the outer wall of the threaded column (12).

4. The modular unmanned aerial vehicle (UAV) with manned / unmanned operation as described in claim 3, characterized in that, The end of the threaded sleeve (13) is connected to the front hatch (2) and the rear hatch (3) via an adapter shaft (14).

5. The modular unmanned aerial vehicle (UAV) with manned / unmanned operation as described in claim 1, characterized in that, The installation mechanism is installed on both ends of the top of the front door mounting platform (17) via a fixed base (23). The fixed base (23) is rotatably provided with a rotating shaft (24). The outer wall of the rotating shaft (24) has a rotatable locking block (25). The inside of the wire transmission operating platform (19) is provided with a slot corresponding to the locking block (25).

6. The modular unmanned aerial vehicle (UAV) with manned / unmanned operation as described in claim 5, characterized in that, The inner wall of the card block (25) is fixed with a rotating ring (26), and both sides of the outer wall of the rotating shaft (24) are fitted with torsion springs (27).

7. The modular unmanned aerial vehicle (UAV) with manned / unmanned operation as described in claim 6, characterized in that, One end of the torsion spring (27) is fixed to the outer wall of the rotating ring (26), and the other end is fixed inside the fixed seat (23).

8. The modular unmanned aerial vehicle (UAV) with manned / unmanned operation as described in claim 7, characterized in that, The top of the fixed base (23) is rotatably provided with a threaded shaft (28), and a handle (29) is fixed at one end of the threaded shaft (28). A limiting plate (30) that matches the thread on the outer wall of the threaded shaft (28) is provided on its outer wall.

9. The modular unmanned aerial vehicle (UAV) with manned / unmanned operation as described in claim 8, characterized in that, The limiting plate (30) is attached to one side of the outer wall of the card block (25), and the other side of the outer wall of the card block (25) slides inside the front door mounting platform (17) and the wire transmission operating platform (19).

10. The modular unmanned aerial vehicle (UAV) with manned / unmanned operation as described in claim 1, characterized in that, The aircraft shell (1) is provided with a line (16) that runs through the interior of the front cabin door (2) and connects to the front door mounting platform (17).

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