A modular aircraft

Abstract

The present invention discloses a modular aircraft, including a flight control module, a power module, a loading module, a power supply module and a parachute module; the number of the power modules is not less than two, and an arm connection structure is provided between each power module and the flight control module; the arm connection structure includes an arm joint arranged on the flight control module and an arm arranged on the power module, and the arm joint and the arm are detachably fixedly connected; the bottom of the flight control module is detachably fixedly connected to the upper end of the loading module; the bottom of the loading module is detachably fixedly connected to the upper end of the power supply module; and the parachute module is installed at the upper end of the flight control module. The structure of the aircraft is simple, the connection relationship between the modules is simple, and the modules can be modularly interchangeable, with high interchangeability, which greatly reduces the production cost.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and particularly relates to a modular aircraft. Background Art

[0002] An unmanned aerial vehicle (UAV) is a type of aircraft. The disadvantage of existing UAV applications is short endurance. Therefore, it is required that the UAV be as lightweight as possible. Usually, the solution adopted is to use carbon fiber materials as much as possible for the fuselage and structural parts. However, carbon fiber materials need to use the process of hot pressing with molds to manufacture components. Conventional carbon fiber tubes and plates are rarely used. Moreover, the part sizes of existing large manned UAVs and cargo UAVs are relatively large, and the cost of mold making is very high. In addition, the connection relationships between various parts on the UAV are very complex, and modular general interchangeability cannot be achieved, resulting in poor interchangeability. Summary of the Invention

[0003] The purpose of the present invention is to overcome the above problems and provide a modular aircraft. The structure of the aircraft is simple, the connection relationships between various modules are simple, and various modules can achieve modular general interchangeability with high interchangeability, greatly reducing the production cost.

[0004] The purpose of the present invention is achieved through the following technical solutions:

[0005] A modular aircraft includes a flight control module for controlling flight, a power module for driving flight, a loading module for loading items or personnel, a power supply module for providing electrical energy, and a parachute module for emergency rescue; wherein,

[0006] The number of the power modules is not less than two, and multiple power modules are evenly distributed along the circumferential direction. An arm connection structure is provided between each power module and the flight control module; the arm connection structure includes an arm joint provided on the flight control module and an arm provided on the power module, and the arm joint and the arm are detachably and fixedly connected.

[0007] The loading module is arranged between the power module and the power supply module. The bottom of the flight control module and the upper end of the loading module are detachably and fixedly connected; the bottom of the loading module and the upper end of the power supply module are detachably and fixedly connected; the parachute module is installed on the upper end of the flight control module.

[0008] The working principle of the above modular aircraft is as follows:

[0009] During operation, the power supply module can provide corresponding electrical energy for the flight control module, the power module, the loading module, and the parachute module. The flight of the aircraft can be controlled through the control module. The power module provides power for flight and drives the aircraft to fly. Through the loading module, items or personnel can be loaded. When loading personnel, the personnel can control the aircraft within the loading module. Since the aircraft is composed of multiple modules, and the modules are detachably and fixedly connected to each other, the various modules of the aircraft can achieve modular general interchangeability, with high interchangeability and simple connection relationships between the modules. When it is necessary to carry people, the loading module that can carry people is replaced. When it is necessary to carry goods, the loading module that can carry goods is replaced. It has high flexibility and is convenient to replace.

[0010] In a preferred embodiment of the present invention, the loading module is a loading cabin, and the loading cabin is a cargo cabin for loading items or a cockpit for carrying people. When it is necessary to fly while loading items, the cargo cabin is detachably and fixedly connected between the power module and the power supply module. When it is necessary to fly with people, the cockpit is detachably and fixedly connected between the power module and the power supply module. In the above structure, by providing a cargo cabin and a cockpit, the cargo cabin or the cockpit can be quickly replaced according to transportation needs, with higher flexibility and stronger interchangeability. Personnel in the cockpit can control the aircraft to fly, and the aircraft can also fly automatically without the need for personnel in the cockpit to control.

[0011] Preferably, the flight control module and the loading module are detachably and fixedly connected through a first locking mechanism. The first locking mechanism includes a male lock provided at the upper end of the loading module and a female lock provided at the bottom of the flight control module. Among them, the upper end of the male lock passes through the bottom of the flight control module and extends upward. A locking groove is provided at the upper end of the male lock. The female lock includes a locking bolt and a locking motor for driving the locking bolt to extend into and out of the locking groove. In the above structure, when it is necessary to disassemble and separate the flight control module and the loading module, the locking bolt is driven to move by the locking motor, the locking bolt extends out of the locking groove, and the locking bolt is separated from the locking groove, so that the flight control module and the loading module can be disassembled and separated. When it is necessary to install and fix the flight control module and the loading module, the upper end of the male lock is passed through the bottom of the flight control module, and then the locking bolt is driven to move by the locking motor. The locking bolt extends into the locking groove, and the locking bolt and the male lock are clamped with each other to achieve locking, thereby realizing the installation and fixation of the flight control module and the loading module. In the above structure, the installation and disassembly are very convenient, improving the interchange efficiency between the modules.

[0012] Furthermore, a first positioning mechanism is provided between the flight control module and the loading module. The first positioning mechanism includes a plurality of positioning pins arranged at the upper end of the loading module and a plurality of positioning holes arranged at the bottom of the flight control module. The positioning pins and the positioning holes correspond to each other one by one and are connected in a matching manner; the axis of the positioning pin is parallel to the axis direction of the male lock. By providing the first positioning mechanism, during installation, the docking between the flight control module and the loading module can be better achieved, with high docking accuracy, convenient positioning, and facilitating the subsequent installation between the two; the axis of the positioning pin is parallel to the axis direction of the male lock, further improving the convenience of positioning and locking.

[0013] Preferably, the loading module and the power supply module are detachably and fixedly connected through a second locking mechanism; a second positioning mechanism is provided between the loading module and the power supply module; wherein, the specific structure of the second locking mechanism is the same as the specific structure of the first locking mechanism, and the specific structure of the second positioning mechanism is the same as the specific structure of the first positioning mechanism. In the above structure, by providing the second locking mechanism, the rapid disassembly, separation, installation, and fixation between the loading module and the power supply module are realized, and the installation and disassembly are very convenient, improving the interchange efficiency between the modules; in addition, by providing the second positioning mechanism, the docking between the loading module and the power supply module can be better achieved, with high docking accuracy, convenient positioning, and facilitating the subsequent installation between the two.

[0014] Preferably, at least two hinge mechanisms are provided between the arm joint and the arm. One end of the hinge mechanism is connected to the arm joint, and the other end is connected to the arm; the hinge shaft of the hinge mechanism is detachable; a protective sleeve is further provided between the arm joint and the arm, and the protective sleeve detachably and fixedly connects the arm joint and the arm. By providing the hinge mechanism, the connection stability between the arm joint and the arm is ensured. By providing the protective sleeve, the connection stability between the arm joint and the arm is further improved; both the protective sleeve and the hinge mechanism are detachably connected, enabling the disassembly and assembly of the power device and the flight control module, realizing modular general interchange; in addition, when the protective sleeve is disassembled, one hinge mechanism between the arm joint and the arm is left undismantled, and each arm can be folded downward, realizing folding and storage, saving the placement space.

[0015] Preferably, the power supply module includes a battery compartment detachably and fixedly connected to the lower end of the loading module and a battery pack arranged in the battery compartment. By providing the above structure, the structure of the battery compartment is simple. After being connected to the lower end of the loading module, the structure becomes very compact, and the aircraft also becomes stable and practical; the battery pack can provide power for the aircraft to fly.

[0016] Preferably, the flight control module includes a flight control cabin detachably and fixedly connected to the upper end of the loading module; inside the flight control cabin, there is a load-bearing mounting frame for mounting the parachute module; the parachute module includes a parachute canopy, a storage box provided on the load-bearing mounting frame for accommodating the parachute canopy, a lid provided on the storage box for encapsulating the parachute canopy, a compression spring for ejecting the parachute canopy, a spring for ejecting the lid, and an automatic buckle device provided on the storage box for locking the lid. By providing the above devices, in case of an emergency, the automatic buckle device opens the lid, and the lid quickly pops open under the action of the spring. At the same time, the compression spring also ejects the parachute canopy, and then the parachute canopy is opened to achieve decelerated landing, ensuring the flight safety of the aircraft.

[0017] Preferably, the power module includes a flight motor provided at the end of the arm and a propeller provided on the flight motor; the flight motor is used to drive the propeller to rotate. With the above structure, the flight motor drives the propeller to rotate, enabling the aircraft to fly.

[0018] Preferably, a recoil device is provided at the bottom of the loading module. The recoil device includes a plurality of recoil rocket launchers; the recoil rocket launchers are fixed to the bottom of the loading module by screws. The jet ports of the recoil rocket launchers are arranged downward. Inside the recoil rocket launcher, there is a thin sheet for sealing the gunpowder powder in the recoil rocket launcher. On the barrel wall of the recoil rocket launcher, there is a spark plug for ignition, and the spark plug is detachably connected to the recoil rocket launcher. By providing the recoil device, in case of an emergency (such as a plane crash), the parachute module is used in case of a crash. When the aircraft falls to a specified distance from the ground (i.e., not far from the ground), the second locking mechanism works, causing the power supply module to separate from the loading module. Then, when approaching the landing point (when the aircraft is about 1 meter from the ground), the spark plug ignites, and the recoil rocket launcher recoils, enabling the aircraft to land safely.

[0019] The present invention has the following beneficial effects compared with the prior art:

[0020] 1. For the modular aircraft in the present invention, each power module and the flight control module are detachably and fixedly connected through the arm connection structure. The bottom of the flight control module and the upper end of the loading module are detachably and fixedly connected. The bottom of the loading module and the upper end of the power supply module are detachably and fixedly connected; for the aircraft of the present invention, the modules are detachably and fixedly connected to each other, enabling the various modules of the aircraft to achieve modular general interchangeability, with high interchangeability, and the connection relationships between the various modules are simple, and the interchange process is simple, fast, and convenient.

[0021] 2. The modular aircraft in the present invention allows for the interchangeability of various modules, which significantly reduces costs, improves the consistency of aircraft products, enhances quality, can compress all aspects of costs arising from differences in the production process, and can also shorten the development cycle of new products and increase market share.

[0022] 3. The modular aircraft in the present invention enables the interchangeability of various modules. When carrying passengers, it can be replaced with a loading module capable of accommodating people, and when carrying goods, it can be replaced with a loading module capable of carrying goods. It has high flexibility, is convenient to replace, and has stronger practicality.

[0023] 4. The modular aircraft in the present invention allows for the interchangeability of various modules. The power module can be replaced to change the load capacity of the aircraft. For example, the power module can be changed from a single - propeller power module to a co - axial dual - propeller power module.

[0024] 5. The modular aircraft in the present invention can replace the parachute module to adapt to the load of the aircraft and ensure the safe flight of the aircraft.

[0025] 6. The modular aircraft in the present invention can replace the power supply module to change the endurance of the aircraft.

[0026] 7. The modular aircraft in the present invention consists of five major modules: a flight control module, a power module, a loading module, a power supply module, and a parachute module, with a simpler and more compact structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a three - dimensional structure schematic diagram of a specific embodiment of a modular aircraft in the present invention.

[0028] Figure 2 It is a three - dimensional structure schematic diagram of the folded state of the arm connection structure of the aircraft in the present invention.

[0029] Figures 3 - 4 It is a schematic diagram of the structure of the aircraft in the present invention with some doors and windows hidden, where, Figure 3 is a three - dimensional view, Figure 4 is a front view.

[0030] Figure 5 is Figure 4 a sectional view taken along the A - A direction in

[0031] Figure 6 It is a three - dimensional structure schematic diagram of the connection between the flight control module and the loading module in the present invention.

[0032] Figure 7 is Figure 6 a partial enlarged view at B in

[0033] Figure 8 Schematic diagram of the installation and connection among part of the flight control module, power module, part of the arm connection structure and parachute module in the present invention.

[0034] Figure 9 is Figure 8 Partial enlarged view at position C in

[0035] Figures 10 - 11 Schematic diagram of the installation and connection among part of the flight control module, part of the first locking mechanism and part of the first positioning mechanism in the present invention, wherein Figure 10 is a perspective view, Figure 11 is a perspective view from another perspective direction.

[0036] Figure 12 Schematic diagram of the installation and connection among the loading module, first locking mechanism and part of the first positioning mechanism in the present invention.

[0037] Figure 13 is Figure 12 Partial enlarged view at position D in

[0038] Figure 14 Stereoscopic structure diagram of the loading module in the present invention.

[0039] Figure 15 Schematic diagram of the installation and connection between the power supply module and the second locking mechanism in the present invention.

[0040] Figure 16 Stereoscopic structure diagram of the parachute module (with the cover hidden) in the present invention.

[0041] Figure 17 Schematic diagram of another embodiment of the power module in the present invention. Detailed implementation manners

[0042] In order to enable those skilled in the art to well understand the technical solution of the present invention, the present invention will be further described below in conjunction with embodiments and drawings, but the implementation manners of the present invention are not limited thereto.

[0043] See Figures 1 - 4 , this embodiment discloses a modular aircraft, including a flight control module 1 for controlling flight, a power module 2 for driving flight, a loading module 3 for loading items or personnel, a power supply module 4 for providing electric energy, and a parachute module 5 for emergency rescue.

[0044] See Figures 1 - 11, the number of the power modules 2 is not less than two, and multiple power modules 2 are evenly distributed along the circumferential direction. An arm connection structure is provided between each power module 2 and the flight control module 1; the arm connection structure includes an arm joint 6 provided on the flight control module 1 and an arm 7 provided on the power module 2, and the arm joint 6 and the arm 7 are detachably and fixedly connected.

[0045] See Figures 1 - 5 , the loading module 3 is arranged between the power module 2 and the power supply module 4, and the bottom of the flight control module 1 and the upper end of the loading module 3 are detachably and fixedly connected; the bottom of the loading module 3 and the upper end of the power supply module 4 are detachably and fixedly connected; the parachute module 5 is installed on the upper end of the flight control module 1, and the parachute module 5 and the flight control module 1 are detachably and fixedly connected.

[0046] See Figures 1 - 5 , the loading module 3 is a loading cabin 8, and the loading cabin 8 is a cargo cabin for loading items or a cockpit for carrying people; when flying for loading items, the cargo cabin is detachably and fixedly connected between the power module 2 and the power supply module 4; when flying for carrying people, the cockpit is detachably and fixedly connected between the power module 2 and the power supply module 4. In the above structure, by providing a cargo cabin and a cockpit, the cargo cabin or the cockpit can be quickly replaced according to the transportation requirements, with higher flexibility and strong interchangeability; the personnel in the cockpit can control the aircraft to fly, and the aircraft can also fly automatically without the control of the personnel in the cockpit.

[0047] There are two loading cabins 8, one is a cargo cabin and the other is a cockpit, and the cargo cabin or the cockpit can be flexibly replaced according to the transportation requirements.

[0048] See Figures 4 - 13, the flight control module 1 and the loading module 3 are detachably and fixedly connected through a first locking mechanism 9; the first locking mechanism 9 includes a male lock 9-1 arranged at the upper end of the loading module 3 and a female lock arranged at the bottom of the flight control module 1; wherein, the upper end of the male lock 9-1 passes through the bottom of the flight control module 1 and extends upward; a locking groove 9-11 is arranged at the upper end of the male lock 9-1; the female lock includes a locking bolt 9-2 and a locking motor 9-3 for driving the locking bolt 9-2 to extend into and out of the locking groove 9-11. In the above structure, when it is necessary to disassemble and separate the flight control module 1 and the loading module 3, the locking bolt 9-2 is driven by the locking motor 9-3 to swing outward, the locking bolt 9-2 extends out of the locking groove 9-11, and the locking bolt 9-2 is separated from the locking groove 9-11, that is, the flight control module 1 and the loading module 3 can be disassembled and separated; when it is necessary to install and fix the flight control module 1 and the loading module 3, the upper end of the male lock 9-1 is passed through the bottom of the flight control module 1, and then the locking bolt 9-2 is driven by the locking motor 9-3 to swing inward, the locking bolt 9-2 extends into the locking groove 9-11, and the locking bolt 9-2 and the male lock 9-1 are clamped with each other to achieve locking, thereby realizing the installation and fixation of the flight control module 1 and the loading module 3; in the above structure, the installation and disassembly are very convenient, and the interchange efficiency between modules is improved.

[0049] See Figures 4 - 13 , the male lock 9-1 is of a columnar structure, the female lock further includes a speed reducer 9-4 arranged between the locking motor 9-3 and the locking bolt 9-2, the input end of the speed reducer 9-4 is connected to the locking motor 9-3, and one end of the locking bolt 9-2 is connected to the output end of the speed reducer 9-4. The housing of the speed reducer 9-4 is fixedly connected to the bottom of the flight control module 1.

[0050] See Figures 4 - 13 , a first positioning mechanism 10 is arranged between the flight control module 1 and the loading module 3, the first positioning mechanism 10 includes a plurality of positioning pins 10-1 arranged at the upper end of the loading module 3 and a plurality of positioning holes 10-2 arranged at the bottom of the flight control module 1, the positioning pins 10-1 and the positioning holes 10-2 are in one-to-one correspondence and are connected in a matching manner; the axis of the positioning pin 10-1 is parallel to the axis direction of the male lock 9-1. By arranging the first positioning mechanism 10, during installation, the docking between the flight control module 1 and the loading module 3 can be better realized, the docking accuracy is high, the positioning is convenient, and it is convenient for the subsequent installation between the two; the axis of the positioning pin 10-1 is parallel to the axis direction of the male lock 9-1, further improving the convenience of positioning and locking.

[0051] The plurality of positioning pins 10-1 are evenly distributed along the circumferential direction, and the number of the positioning pins 10-1 is three.

[0052] SeeFigures 4 - 15 The loading module 3 and the power supply module 4 are detachably and fixedly connected through a second locking mechanism 11; a second positioning mechanism 12 is arranged between the loading module 3 and the power supply module 4; wherein, the specific structure of the second locking mechanism 11 is the same as that of the first locking mechanism 9, and the specific structure of the second positioning mechanism 12 is the same as that of the first positioning mechanism 10. In the above structure, by setting the second locking mechanism 11, the rapid disassembly, separation, installation and fixation between the loading module 3 and the power supply module 4 are realized, the installation and disassembly are very convenient, and the interchange efficiency between modules is improved; in addition, by setting the second positioning mechanism 12, the docking between the loading module 3 and the power supply module 4 can be better realized, the docking accuracy is high, the positioning is convenient, and the subsequent installation between the two is facilitated.

[0053] See Figures 14 - 15 For the second locking mechanism 11, the male lock 9-1 is arranged at the upper end of the power supply module 4, and the female lock of the second locking mechanism 11 is arranged at the bottom of the loading module 3; for the second positioning mechanism 12, the positioning pin 10-1 is arranged at the upper end of the power supply module 4, and the positioning hole 10-2 is arranged at the bottom of the loading module 3. The purpose is to make the disassembly and assembly of the loading module 3 and the power supply module 4 more convenient.

[0054] See Figures 4 - 15 The axis of the male lock 9-1 is collinear with the axis of the loading cabin 8.

[0055] See Figures 4 - 15 For the power supply module 4 and the loading module 3, a pair of cable connectors 13 are fixedly arranged between the upper end of the power supply module 4 and the bottom of the loading module 3. The positions of the two cable connectors 13 correspond to each other and are inserted into each other. By setting the cable connectors 13, the electrical connection between the power supply module 4 and the loading module 3 is realized, and power is provided for the electrical equipment in the loading module 3; a pair of cable connectors 13 are also arranged between the bottom of the flight control module 1 and the upper end of the loading module 3, and this cable connector 13 can realize the electrical connection between the flight control module 1 and the loading module 3.

[0056] See Figures 1 - 10, at least two hinge mechanisms 14 are provided between the arm joint 6 and the arm 7. One end of the hinge mechanism 14 is connected to the arm joint 6, and the other end is connected to the arm 7; the hinge shaft of the hinge mechanism 14 is detachable; a protective sleeve 15 is further provided between the arm joint 6 and the arm 7, and the protective sleeve 15 detachably and fixedly connects the arm joint 6 and the arm 7. By providing the hinge mechanism 14, the connection stability between the arm joint 6 and the arm 7 is ensured. By providing the protective sleeve 15, the connection stability between the arm joint 6 and the arm 7 is further improved; both the protective sleeve 15 and the hinge mechanism 14 are detachably connected, which can realize the disassembly and assembly of the power device and the flight control module 1, and realize modular general interchangeability; in addition, when the protective sleeve 15 is disassembled, one hinge mechanism 14 between the arm joint 6 and the arm 7 is not disassembled, and each arm 7 can be folded downward to realize folding storage and save the placement space.

[0057] See Figures 1 - 10 , the arm joint 6 is provided with a first wire docking head 16 originating from the flight control module 1, and the arm 7 is provided with a second wire docking head 17 originating from the power module 2, and the first wire docking head 16 is inserted into the second wire docking head 17. By providing the first wire docking head 16 and the second wire docking head 17, it is convenient for the electrical connection between the flight control module 1 and the power module 2 after the power module 2 is replaced. Cooperating with two pairs of cable connectors 13, the electrical connection between the power supply module 4 and the loading module 3, the flight control module 1, and the power module 2 can be realized.

[0058] See Figures 1 - 5 and Figure 15 , the power supply module 4 includes a battery compartment 4-1 detachably and fixedly connected to the lower end of the loading module 3 and a battery pack 4-2 arranged in the battery compartment 4-1. By providing the above structure, the structure of the battery compartment 4-1 is simple. After being connected to the lower end of the loading module 3, the structure becomes very compact, and the aircraft also becomes stable and practical; the battery pack 4-2 can provide power for the aircraft to fly.

[0059] See Figures 1 - 11 and Figure 16, the flight control module 1 includes a flight control cabin 1-1 detachably and fixedly connected to the upper end of the loading module 3; inside the flight control cabin 1-1, there is a load-bearing mounting frame 18 for mounting the parachute module 5; the parachute module 5 includes a parachute canopy 5-1, a storage box 5-2 arranged on the load-bearing mounting frame 18 for accommodating the parachute canopy 5-1, a lid 5-3 arranged on the storage box 5-2 for encapsulating the parachute canopy 5-1, a compression spring for ejecting the parachute canopy 5-1, a spring 5-4 for ejecting the lid 5-3, and an automatic buckle device 5-5 arranged on the storage box 5-2 for locking the lid 5-3; wherein, the compression spring is arranged between the parachute canopy 5-1 and the bottom of the storage box 5-2, and the spring 5-4 acts on the storage box 5-2 and the lid 5-3. By setting the above devices, in case of an emergency, the automatic buckle device 5-5 opens the lid 5-3, the lid 5-3 quickly bounces open under the action of the spring 5-4, and at the same time the compression spring also ejects the parachute canopy 5-1, and then the parachute canopy 5-1 is opened to achieve decelerated landing, ensuring the flight safety of the aircraft.

[0060] See Figures 1 - 11 and Figure 16 , the automatic buckle device 5-5 can realize automatic unbuckling by controlling the reciprocating movement of the buckle member through an electromagnet or a servo. One end of the lid 5-3 is connected to the storage box 5-2 through a hinge structure 5-6, and the other end is connected to the storage box 5-2 through the automatic buckle device 5-5.

[0061] See Figures 6 - 8 , the storage box 5-2 is detachably and fixedly connected to the load-bearing mounting frame 18 through bolts, which is convenient for the disassembly and assembly of the parachute module 5 and improves the interchangeability.

[0062] See Figures 1 - 5 , the flight control module 1 further includes a control device arranged inside the flight control cabin 1-1 for controlling flight, and the specific structure of the control device can refer to the prior art.

[0063] See Figures 1 - 8 , the power module 2 includes a flight motor 2-1 arranged at the end of the arm 7 and a propeller 2-2 arranged on the flight motor 2-1; the flight motor 2-1 is used to drive the propeller 2-2 to rotate. Through the above structure, the flight motor 2-1 drives the propeller 2-2 to rotate, and the flight of the aircraft can be realized.

[0064] See Figures 1 - 8 and Figure 17, in this embodiment, the number of the power modules 2 is six, and each power module 2 is a single-propeller power module, that is, the propeller 2-2 of the power module 2 is one. The power module 2 in this embodiment can also be a coaxial dual-propeller power module, that is, the propeller 2-2 of the power module 2 is two, which are distributed up and down. The specific structure is as Figure 17 shown. Since each module can be interchanged, therefore, according to the transportation requirements, the power module 2 can be replaced to change the load capacity of the aircraft. The number of the power modules 2 in this embodiment can also be twelve.

[0065] See Figure 5 and Figure 14 , a recoil device is provided at the bottom of the loading module 3. The recoil device includes a plurality of recoil rocket launchers 19; the recoil rocket launchers 19 are fixed to the bottom of the loading module 3 by screws. The jet ports of the recoil rocket launchers 19 are arranged downward. A thin sheet is provided inside the recoil rocket launcher 19 to seal the gunpowder powder in the recoil rocket launcher 19; a spark plug for ignition is provided on the barrel wall of the recoil rocket launcher 19, and the spark plug is detachably connected to the recoil rocket launcher 19. By providing the recoil device, when an emergency occurs (such as a plane crash), the parachute module 5 is used in the case of a plane crash. When the aircraft falls to a specified distance from the ground (that is, when it is not far from the ground, for example, about 20 - 30 meters), the second locking mechanism 11 works to separate the power supply module 4 from the loading module 3. Then, when approaching the landing point (when the aircraft is about 1 meter from the ground), the spark plug ignites, and the recoil rocket launcher 19 recoils, so that the aircraft can land safely.

[0066] Furthermore, the number of the recoil rocket launchers 19 is four, and they are fixed to the bottom of the loading cabin 8 by screws.

[0067] See Figures 1 - 5 , a plurality of landing legs 20 are provided at the lower end of the loading cabin 8, and the plurality of landing legs 20 are evenly distributed along the circumferential direction. By providing the landing legs 20, the aircraft can be placed, and the plurality of landing legs 20 can play a role in stable placement. Specifically, the number of the landing legs 20 is 3.

[0068] See Figures 1 - 15 , the male lock 9-1 of the first locking mechanism 9 is arranged at the upper end of the loading cabin 8, and the female lock is arranged at the bottom of the flight control cabin 1-1; the positioning pin 10-1 of the first positioning mechanism 10 is arranged at the upper end of the loading cabin 8, and the positioning hole 10-2 is arranged at the bottom of the flight control cabin 1-1; the male lock 9-1 of the second locking mechanism 11 is arranged at the upper end of the battery cabin 4-1, and the female lock is arranged at the bottom of the loading cabin 8; the positioning pin 10-1 of the second positioning mechanism 12 is arranged at the upper end of the battery cabin 4-1, and the positioning hole 10-2 is arranged at the bottom of the loading cabin 8.

[0069] See Figures 1 - 15 , in the aircraft of this embodiment, the loading module 3 is the loading cabin 8, the flight control module 1 includes the flight control cabin 1-1, the power supply module 4 includes the battery cabin 4-1, and the joints between the modules are cabin joints. After installation, the structure becomes very compact.

[0070] In the modular aircraft of this embodiment, the parachute module 5 has different specifications, and the parachute module 5 can be replaced to adapt to the load of the aircraft and ensure the safe flight of the aircraft.

[0071] In the modular aircraft of this embodiment, the power supply module 4 has different specifications, and the power supply module 4 can be replaced to change the endurance of the aircraft.

[0072] See Figures 1 - 11 , the working principle of the above modular aircraft is:

[0073] During operation, the power supply module 4 can provide corresponding electrical energy for the flight control module 1, the power module 2, the loading module 3 and the parachute module 5. The aircraft can be controlled through the control module. The power module 2 provides power for flight and drives the aircraft to fly. Items or personnel can be loaded through the loading module 3. When loading personnel, the personnel can control the aircraft inside the loading module 3. Since the aircraft is composed of multiple modules, and the modules are detachably and fixedly connected to each other, the various modules of the aircraft can achieve modular general interchange, with high interchangeability and simple connection relationships between the modules; when it is necessary to carry people, the loading module 3 that can carry people is replaced, and when it is necessary to carry goods, the loading module 3 that can carry goods is replaced, with high flexibility and convenient replacement.

[0074] The above is a preferred embodiment of the present invention, but the embodiments of the present invention are not limited to the above content. Any other changes, modifications, substitutions, combinations, and simplifications made without departing from the spirit and principle of the present invention shall be equivalent replacement methods and are all included in the protection scope of the present invention.

Claims

1. A modular aircraft, characterized in that, it includes a flight control module for controlling flight, a power module for driving flight, a loading module for loading items or personnel, a power supply module for providing electrical energy, and a parachute module for emergency rescue; wherein, the number of the power modules is not less than two, and multiple power modules are evenly distributed along the circumferential direction. An arm connection structure is provided between each power module and the flight control module; the arm connection structure includes an arm joint provided on the flight control module and an arm provided on the power module, and the arm joint and the arm are detachably and fixedly connected; the loading module is arranged between the power module and the power supply module, and is detachably and fixedly connected between the bottom of the flight control module and the upper end of the loading module; and is detachably and fixedly connected between the bottom of the loading module and the upper end of the power supply module; the parachute module is installed at the upper end of the flight control module; the flight control module and the loading module are detachably and fixedly connected through a first locking mechanism; the first locking mechanism includes a male lock provided at the upper end of the loading module and a female lock provided at the bottom of the flight control module; wherein, the upper end of the male lock passes through the bottom of the flight control module and extends upward; a locking groove is provided at the upper end of the male lock; the female lock includes a locking bolt and a locking motor for driving the locking bolt to extend into and out of the locking groove; a first positioning mechanism is provided between the flight control module and the loading module, and the first positioning mechanism includes a plurality of positioning pins provided at the upper end of the loading module and a plurality of positioning holes provided at the bottom of the flight control module, and the positioning pins and the positioning holes correspond to each other and are connected in a matching manner; the axis of the positioning pin is parallel to the axis direction of the male lock; at least two hinge mechanisms are provided between the arm joint and the arm, one end of the hinge mechanism is connected to the arm joint, and the other end is connected to the arm; the hinge shaft of the hinge mechanism is detachable; a protective sleeve is also provided between the arm joint and the arm, and the protective sleeve detachably and fixedly connects the arm joint and the arm; a first wire docking head originating from the flight control module is provided on the arm joint, and a second wire docking head originating from the power module is provided on the arm, and the first wire docking head and the second wire docking head are plugged; the flight control module includes a flight control cabin detachably and fixedly connected to the upper end of the loading module; a load-bearing mounting frame is provided inside the flight control cabin, and the load-bearing mounting frame is used for mounting the parachute module; the parachute module includes a parachute canopy, a storage box provided on the load-bearing mounting frame for accommodating the parachute canopy, a lid provided on the storage box for encapsulating the parachute canopy, a compression spring for ejecting the parachute canopy, a spring for ejecting the lid, and an automatic buckle device provided on the storage box for locking the lid.

2. The modular aircraft according to claim 1, characterized in that, The loading module is a loading cabin, and the loading cabin is a cargo cabin for loading items or a cockpit for carrying people; when flying with items to be loaded, the cargo cabin is detachably and fixedly connected between the power module and the power supply module; when flying with people, the cockpit is detachably and fixedly connected between the power module and the power supply module.

3. A modular aircraft according to claim 1, wherein, the loading module and the power supply module are detachably and fixedly connected through a second locking mechanism; a second positioning mechanism is arranged between the loading module and the power supply module; wherein, the specific structure of the second locking mechanism is the same as that of the first locking mechanism, and the specific structure of the second positioning mechanism is the same as that of the first positioning mechanism.

4. A modular aircraft according to claim 1, wherein, the power supply module includes a battery compartment detachably and fixedly connected to the lower end of the loading module and a battery pack arranged in the battery compartment; at the upper end of the power supply module and the bottom of the loading module, paired cable connectors are fixedly arranged, and the positions of the two cable connectors correspond to each other and are inserted into each other.

5. A modular aircraft according to claim 1, wherein, the power module includes a flight motor arranged at the end of the arm and a propeller arranged on the flight motor; the flight motor is used to drive the propeller to rotate.

6. A modular aircraft according to claim 1, wherein, a recoil device is arranged at the bottom of the loading module, and the recoil device includes a plurality of recoil rocket launchers; the recoil rocket launchers are fixed to the bottom of the loading module by screws, the jet ports of the recoil rocket launchers are arranged downward, a thin sheet is arranged inside the recoil rocket launcher to seal the gunpowder powder in the recoil rocket launcher; a spark plug for ignition is arranged on the barrel wall of the recoil rocket launcher, and the spark plug is detachably connected to the recoil rocket launcher.

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