A multi-takeoff mode aircraft

Abstract

This invention discloses a multi-takeoff mode aircraft, comprising a flight rotor module, a wing folding and switching module, a connecting module, a support module, a landing gear folding and switching module, a base fixing module, a nose module, and landing gear. The nose module, connecting module, support module, and base fixing module are arranged sequentially along the axial direction of the aircraft. The wing folding and switching module is connected to the connecting module and the nose module, allowing the flight rotor module to have both deployed and folded states through cooperation with the wing folding and switching module. The landing gear folding and switching module is connected to the connecting module, support module, and base fixing module, allowing the landing gear to have both deployed and folded states through cooperation with the landing gear folding and switching module. In the first takeoff mode, the flight rotor module and landing gear are initially in the deployed state; in the second takeoff mode, the flight rotor module and landing gear are initially in the folded state. This invention's aircraft supports not only traditional ground takeoff modes but also catapult takeoff modes.

Description

Technical Field

[0001] This invention relates to a multi-takeoff mode aircraft, belonging to the field of aircraft. Background Technology

[0002] Drones are currently the most diverse and widely used type of aircraft, exhibiting great diversity in multiple dimensions such as structure, function, size, flight altitude, and speed. Fixed-wing drones are known for their long endurance, high flight speed, and powerful payload capacity; unmanned helicopters are characterized by their hovering ability, high flexibility, and unique high-altitude shooting perspective; while rotary-wing micro-drones stand out for their small size, vertical take-off and landing capabilities, and ultra-low-speed flight.

[0003] Traditional drones are slow to deploy and inefficient. Drones rely on their own performance to reach the work location, but limited takeoff speed and energy increase deployment time, making it impossible to respond and deploy quickly in emergency situations. Existing rotary-wing drones also suffer from problems such as low endurance, inconvenience in carrying, and high cost.

[0004] In view of this, the present invention is hereby proposed. Summary of the Invention

[0005] This invention provides a multi-takeoff mode aircraft that supports not only the traditional ground takeoff mode but also the catapult takeoff mode, thereby adapting to different takeoff environments and requirements to achieve rapid response and deployment in emergency situations.

[0006] The technical solution of this invention is:

[0007] A multi-takeoff-mode aircraft includes a flight rotor module 1, a wing folding and switching module 2, a connecting module 3, a support module 4, a landing gear folding and switching module 5, a base fixing module 6, a nose module 7, and landing gear 36. The nose module 7, the connecting module 3, the support module 4, and the base fixing module 6 are arranged sequentially along the axial direction of the aircraft. The wing folding and switching module 2 is connected to the connecting module 3 and the nose module 7. By cooperating with the wing folding and switching module 2, the flight rotor module 1 can have a first deployed state and a first folded state. The landing gear folding switching module 5 is connected to the connecting module 3, the bracket module 4, and the base fixing module 6. By cooperating with the landing gear 36 and the landing gear folding switching module 5, the landing gear 36 can have a second deployed state and a second folded state. When the aircraft adopts the first takeoff mode, the initial state of the flight rotor module 1 is the first deployed state, and the initial state of the landing gear 36 is the second deployed state. When the aircraft adopts the second takeoff mode, the initial state of the flight rotor module 1 is the first folded state, and the initial state of the landing gear 36 is the second folded state.

[0008] Furthermore, the number of the flight rotor module 1, wing folding switching module 2, landing gear folding switching module 5, and landing gear 36 are equal, and multiple modules are provided.

[0009] Furthermore, the flight rotor module 1 includes an arm 8, a DC motor 11, a folding propeller 12, a DC motor mounting bracket 13, and a folding propeller mounting bracket 14; one end of the DC motor 11 is mounted with the folding propeller 12 via the folding propeller mounting bracket 14, and the other end of the DC motor 11 is fixed to one end of the arm 8 via the DC motor mounting bracket 13, and the other end of the arm 8 cooperates with the wing folding switching module 2.

[0010] Furthermore, the wing folding switching module 2 includes a first bolt 15, a first bolt fixing nut 16, a double torsion spring 17, and an arm bracket 31. The first bolt 15 passes sequentially from one end to the other through the first arm bracket 31, one side of the double torsion spring 17, the arm 8 of the flight rotor module 1, the other side of the double torsion spring 17, and the second arm bracket 31 before being fixed by the first bolt fixing nut 16. The arm brackets 31 are arranged on opposite sides along the axial direction of the aircraft for connecting the nose module 7 and the connecting module 3. An extension 9 is provided on the opposite side of the two arm brackets 31, and the extension 9 is provided with a first through hole 10 for the end of the double torsion spring 17 to extend into. A slot is provided on the outer side of the arm 8 for fixing the double torsion spring 17.

[0011] Furthermore, the connection module 3 includes an arm support fixing base 34 and a lower half of the battery compartment 35; the arm support fixing base 34 is connected to the landing gear bracket 39 in the landing gear folding switching module 5 via a fixing member, and is connected to one side of the arm support 31 in the wing folding switching module 2 via a fixing member; the lower half of the battery compartment 35 is attached to the side of the arm support fixing base 34 near the nose module 7.

[0012] Furthermore, the landing gear folding and switching module 5 includes a single torsion spring 20, a second bolt 18, a second bolt fixing nut 19, and a landing gear bracket 39; the top of the landing gear bracket 39 is connected to the boom bracket fixing base 34 in the connecting module 3, the middle is connected to the bracket module 4, and the bottom is connected to the base fixing module 6; the second bolt 18 passes through the through hole on one side of the landing gear bracket 39 away from the nose module 7, the through hole on one side of the landing gear 36, the single torsion spring 20, the through hole on the other side of the landing gear 36, and the through hole on the other side of the landing gear bracket 39 away from the nose module 7, and is then fixed by the second bolt fixing nut 19.

[0013] Furthermore, the landing gear bracket 39 is provided with a second through hole 23 for connecting the bracket module 4, a third through hole 24 for fixing one end of the single torsion spring 20, a recessed hole 25 for embedding and fixing the thermoplastic nut, a baffle 26 for limiting the landing gear 36, a limiting tenon 27 for cooperating with the seat fixing module 6, and a screw hole 28 for connecting with the arm bracket fixing base 34; the bracket module 4 and the landing gear bracket 39 are connected by a bolt 21 passing through the fourth through hole 29 of the bracket module 4 and the second through hole 23 of the landing gear bracket 39 and a nut 22; the flight controller is installed on the bracket module 4; one end of the single torsion spring 20 is connected to the third through hole 24 of the landing gear bracket 39, and the other end of the third through hole 24 is connected to the through hole of the landing gear 36; the landing gear bracket 39 and the base fixing module 6 are fixed by the limiting tenon 27 cooperating with the limiting hole 42 of the base fixing module 6 and by heating and fixing the thermoplastic nut to the landing gear bracket 39.

[0014] Furthermore, the base fixing module 6 includes a base fixing plate 40, on which a limiting hole 42 is provided to cooperate with the landing gear bracket 39 in the landing gear folding and switching module 5.

[0015] Furthermore, the head module 7 includes an arm support fixing top 30, a conical cover 43, a GPS module fixing seat 44, and an upper battery compartment 45; the non-pointed end of the conical cover 43 is connected to the arm support fixing top 30; the upper battery compartment 45 is provided on the side of the arm support fixing top 30 facing the conical cover 43, and the upper battery compartment 45 is combined with the lower battery compartment 35 in the connecting module 3 to form a complete battery compartment; the GPS module fixing seat 44 is built into the conical cover 43 and covers the upper battery compartment 45.

[0016] The beneficial effects of this invention are:

[0017] First, this invention enables the switching between deployed and folded states of the flight rotor module and landing gear through the coordinated operation of the flight rotor module and wing folding switching module, as well as the landing gear folding switching module and landing gear. Based on this switching method, not only can takeoff be performed in different takeoff modes to adapt to different takeoff requirements, but also the deployment and folding of the rotor and landing gear solves the problem of the rotor not being able to be folded, allowing it to be folded up when not in use for easy portability. Furthermore, the flight rotor module can quickly deploy during catapult launch, enabling it to adapt to takeoff in different takeoff environments.

[0018] Secondly, this invention designs a connection module and a support module that are responsible for connecting the various parts of the aircraft. Furthermore, by placing the flight controller and battery on top of the module, not only is space used efficiently, but the center of gravity of the entire aircraft is also ensured to be in the middle position, thus avoiding the problem of being top-heavy.

[0019] Third, the present invention also introduces a nose module structure that places the GPS module inside a semi-elliptical nose cone at the top of the aircraft. This structural design not only avoids signal interference, but the semi-elliptical shape can also effectively reduce the impact of wind resistance during impact and ejection.

[0020] Fourth, the overall structure of this invention is simple and clear, compact and lightweight, which not only makes it easy to carry and operate, but also reduces manufacturing costs to the greatest extent through its simplified structure, achieving a perfect combination of high efficiency and high cost performance. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the overall unfolded state of the present invention;

[0022] Figure 2 This is a schematic diagram of the overall folding of the present invention;

[0023] Figure 3 This is a schematic diagram of the flight rotor module of the present invention;

[0024] Figure 4 This is an assembly diagram of the flight rotor module, wing folding switching module, and connection module of the present invention;

[0025] Figure 5 A partial enlargement of the assembly of the flight rotor module and wing folding switching module of the present invention. Figure 1 ;

[0026] Figure 6 A partial enlargement of the assembly of the flight rotor module and wing folding switching module of the present invention. Figure 2 ;

[0027] Figure 7 This is an exploded view of the wing folding switching module of the present invention;

[0028] Figure 8 This is a schematic diagram of the boom support of the present invention;

[0029] Figure 9 This is a schematic diagram of the connection module of the present invention;

[0030] Figure 10 This is a schematic diagram of the assembly of the landing gear folding switching module and the landing gear of the present invention;

[0031] Figure 11 This is an exploded view of the landing gear folding switching module and the landing gear of the present invention;

[0032] Figure 12 This is a schematic diagram of the landing gear support of the present invention;

[0033] Figure 13 This is a schematic diagram of the assembly of the support module and the landing gear support of the present invention;

[0034] Figure 14 This is a schematic diagram of the support module of the present invention;

[0035] Figure 15 This is a schematic diagram of the base fixing module of the present invention;

[0036] Figure 16 This is an exploded view of the nose module of the present invention;

[0037] Figure 17 This is a schematic diagram of the installation of the head unit module of the present invention;

[0038] The following are the labels in the diagram: 1-Flight rotor module, 2-Wing folding switching module, 3-Connecting module, 4-Bracket module, 5-Landing gear folding switching module, 6-Base fixing module, 7-Nose module, 8-Arm, 9-Extension, 10-First through hole, 11-DC motor, 12-Folding propeller, 13-DC motor fixing component, 14-Folding propeller fixing component, 15-First bolt, 16-First bolt fixing nut, 17-Double torsion spring, 18-Second bolt, 19-Second bolt fixing nut, 20-Single torsion spring, 21-... 22-Bolt, 23-Second through hole, 24-Third through hole, 25-Buried hole, 26-Baffle, 27-Limit tenon, 28-Screw hole, 29-Fourth through hole, 30-Arm bracket fixing top seat, 31-Arm bracket, 32-Second opening slot, 33-Third opening slot, 34-Arm bracket fixing base, 35-Lower half of battery compartment, 36-Landing gear, 39-Landing gear bracket, 40-Base fixing plate, 41-Camera mounting base, 42-Limit hole, 43-Conical cover, 44-GPS module mounting base, 45-Upper half of battery compartment. Detailed Implementation

[0039] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. 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. It should be noted that, unless otherwise specified, the embodiments and features in the embodiments of this application can be arbitrarily combined with each other.

[0040] This invention provides a multi-takeoff mode aircraft, which includes at least a first takeoff mode and a second takeoff mode. Exemplarily, the first takeoff mode is a ground takeoff mode; the second takeoff mode is a catapult takeoff mode. The following describes an embodiment of the first takeoff mode:

[0041] Example 1: Figure 1-17As shown, a multi-takeoff mode aircraft includes a flight rotor module 1, a wing folding and switching module 2, a connecting module 3, a support module 4, a landing gear folding and switching module 5, a base fixing module 6, a nose module 7, and landing gear 36. The nose module 7, the connecting module 3, the support module 4, and the base fixing module 6 are arranged sequentially along the axial direction of the aircraft. The wing folding and switching module 2 is connected to the connecting module 3 and the nose module 7. By cooperating with the wing folding and switching module 2, the flight rotor module 1 can have a first deployed state and a first folded state. The landing gear folding switching module 5 is connected to the connecting module 3, the bracket module 4, and the base fixing module 6. By cooperating with the landing gear 36, the landing gear 36 can have a second deployed state and a second folded state. When the aircraft adopts the first takeoff mode, the initial state of the flight rotor module 1 is the first deployed state, and the initial state of the landing gear 36 is the second deployed state. When the aircraft adopts the second takeoff mode, the initial state of the flight rotor module 1 is the first folded state, and the initial state of the landing gear 36 is the second folded state.

[0042] As can be seen from the above technical solution, the landing gear folding switching module 5 is located at the bottom of the aircraft. On the one hand, it supports the entire fuselage before ground flight, and on the other hand, it can play a buffering role when the aircraft lands.

[0043] Furthermore, the number of the flight rotor module 1, wing folding switching module 2, landing gear folding switching module 5, and landing gear 36 are equal, and multiple modules are provided.

[0044] Furthermore, such as Figure 3 As shown, the multiple flight rotor modules 1 have the same structure, each including an arm 8, a DC motor 11, a folding propeller 12, a DC motor mounting bracket 13, and a folding propeller mounting bracket 14; one end of the DC motor 11 is equipped with a folding propeller 12 through the folding propeller mounting bracket 14, and the other end of the DC motor 11 is fixed to one end of the arm 8 through the DC motor mounting bracket 13, and the other end of the arm 8 cooperates with the wing folding switching module 2.

[0045] For example, such as Figure 3 As shown, the folding propeller 12 is divided into a forward propeller and a reverse propeller, with each flight rotor module 1 equipped with one forward propeller or one reverse propeller. There are four flight rotor modules 1, meaning that the number of forward and reverse propellers is the same throughout the entire catapult aircraft. This avoids the problem of unbalanced aerodynamic torque caused by an odd number of propellers, thus ensuring the normal flight of the aircraft.

[0046] Furthermore, such as Figures 4-8As shown, the multiple wing folding switching modules 2 have the same structure, each including a first bolt 15, a first bolt fixing nut 16, a double torsion spring 17, and an arm bracket 31. The first bolt 15 passes sequentially from one end to the other through the first arm bracket 31, one side of the double torsion spring 17, the arm 8 of the flight rotor module 1, the other side of the double torsion spring 17, and the second arm bracket 31 before being fixed by the first bolt fixing nut 16. The arm brackets 31 are arranged on opposite sides along the axial direction of the aircraft to connect the nose module 7 and the connecting module 3. The two opposing sides of the two arm brackets 31 are provided with an extension 9, which has a first through hole 10 for the end of the double torsion spring 17 to extend into. The outer side of the arm 8 is provided with a slot for fixing the double torsion spring 17. In the above, the first bolt fixing nut 16 is used to fix the first bolt 15 to ensure that the arm 8 can be stably fixed on the arm bracket 31.

[0047] Furthermore, such as Figure 8 As shown, the first through hole 10 on the arm support 31 is designed to fix the torsion spring. When the arm 8 is folded downwards, the two ends of the double torsion spring 17 are subjected to a downward force, which causes the double torsion spring 17 to gradually loosen. Therefore, when the arm 8 is deployed, the expected balance may not be achieved. To solve this problem, the second through hole on the arm support 31 is designed with a certain slope (i.e., the tilt angle between the axis of the through hole and the horizontal direction is 5°-10°, preferably 5°). When the aircraft is in the first state (deployed state), this slope allows the torsion spring to be subjected to a certain preload, thereby enabling the arm to maintain a more stable state during flight.

[0048] Furthermore, such as Figure 9 As shown, the connection module 3 includes an arm support mounting base 34 and a lower battery compartment portion 35. The arm support mounting base 34 is connected to the landing gear bracket 39 in the landing gear folding switching module 5 via a fastener, and is also connected to one side of the arm support 31 in the wing folding switching module 2 via a fastener. The lower battery compartment portion 35 is attached to the side of the arm support mounting base 34 near the nose module 7, i.e., the side where the arm support 31 is installed. Furthermore, in practical use, the contact area between the arm 8 and the arm support mounting base 34 can be coated with 3M adhesive. Based on this method, a good shock absorption effect is provided for the arm during flight, thereby greatly improving flight stability.

[0049] Furthermore, such as Figures 10-13As shown, the multiple landing gear folding and switching modules 5 have the same structure, each including a single torsion spring 20, a second bolt 18, a second bolt fixing nut 19, and a landing gear bracket 39. The top of the landing gear bracket 39 is connected to the boom bracket fixing base 34 in the connecting module 3, the middle is connected to the bracket module 4, and the bottom is connected to the base fixing module 6. The second bolt 18 passes through the through hole on one side of the landing gear bracket 39 away from the nose module 7, the through hole on one side of the landing gear 36, the single torsion spring 20, the through hole on the other side of the landing gear 36, and the through hole on the other side of the landing gear bracket 39 away from the nose module 7, and is then fixed by the second bolt fixing nut 19.

[0050] In the above-mentioned configuration, the first and second plug bolts 15 and 18 are plug screws. These screws provide precise positioning and effectively prevent relative movement or loosening of the torsion spring under stress or vibration, thus ensuring the stability and reliability of the system. When fixing the torsion spring, appropriate tightening force ensures the connection strength between the torsion spring and the fixed component, preventing malfunctions or accidents caused by loose connections. Furthermore, the smooth shaft section of the plug screw reduces friction with the torsion spring, minimizing wear.

[0051] Furthermore, such as Figure 12-14 As shown, the landing gear bracket 39 is provided with a second through hole 23 for connecting the bracket module 4, a third through hole 24 for fixing one end of the single torsion spring 20, a buried hole 25 for embedding and fixing the hot melt nut, a baffle 26 for limiting the landing gear 36, a limiting tenon 27 for cooperating with the seat fixing module 6, and a screw hole 28 for connecting with the boom bracket fixing base 34.

[0052] The bracket module 4 is connected to the landing gear bracket 39 by means of bolt 21 passing through the fourth through hole 29 of the bracket module 4 and the second through hole 23 of the landing gear bracket 39 and by means of nut 22; the bracket module 4 is used to install the flight controller;

[0053] One end of the single torsion spring 20 is connected to the third through hole 24 of the landing gear bracket 39, and the other end of the third through hole 24 is connected to the through hole of the landing gear 36.

[0054] The landing gear bracket 39 is fixed to the base fixing module 6 by engaging the limiting tenon 27 with the limiting hole 42 of the base fixing module 6 and then fixing the hot melt nut on the landing gear bracket 39 by heating.

[0055] As can be seen from the above technical solution, when both ends of the single torsion spring 20 are fixed, the landing gear 36 can fold and unfold by relying on the elasticity of the torsion spring, which not only facilitates catapult takeoff but also greatly saves storage space. The heat-fused nut, which is fixed to the landing gear bracket 39, makes it easier to fix the landing gear bracket 39 to the base fixing module 6. The limiting baffle on the landing gear 36 can effectively block the landing gear, preventing it from moving or folding unnecessarily, thereby enhancing the overall stability. The limiting tenon connected to the base fixing module 6 ensures the stability and accuracy of the connection when the landing gear bracket 39 is connected to the base fixing module 6, preventing loosening or displacement during flight. The fastening action of bolts 21 and nuts 22 achieves a stable connection between the support module 4 and the landing gear support 39, firmly fixing the flight controller to the support module 4 to ensure its stable operation. At the same time, the support module 4 is located between the arm support fixing base 34 and the base fixing module 6. This layout not only makes reasonable use of the limited space, but also provides effective protection for the flight controller.

[0056] Furthermore, such as Figure 15 As shown, the base fixing module 6 includes a base fixing plate 40 and a camera mounting bracket 41. The base fixing plate 40 has a limiting hole 42 that mates with the landing gear bracket 39 in the landing gear folding and switching module 5. The camera mounting bracket 41 is located on the side of the base fixing plate 40 facing the bracket module 4. Applying the above technical solution, it can be seen that the base fixing plate 40 mates with a specially designed limiting tenon on the landing gear bracket 39, and is further reinforced by the embedded holes of the fixing thermosetting nuts on the landing gear bracket 39. This connection method ensures the stability and reliability between the base fixing module 6 and the landing gear bracket 39. Simultaneously, the camera mounting bracket 41 uses electrical tape or other fixing methods to firmly fix the camera to the camera mounting bracket 41 to prevent loosening or displacement during flight. This design ensures the stability of the camera and facilitates the installation and removal of the camera.

[0057] Furthermore, such as Figure 16-17As shown, the nose module 7 includes an arm support mounting top 30, a conical cover 43, a GPS module mounting base 44, and an upper battery compartment 45. The non-pointed end of the conical cover 43 is connected to the arm support mounting top 30. The upper battery compartment 45 is located on the side of the arm support mounting top 30 facing the conical cover 43. The upper battery compartment 45 is combined with the lower battery compartment 35 in the connecting module 3 to form a complete battery compartment. The GPS module mounting base 44 is built into the conical cover 43 and covers the upper battery compartment 45. In the above technical solution, the conical cover 43 is tightly connected to the arm support mounting top 30 by fasteners or buckles, forming a robust and streamlined nose structure. This design not only enhances the overall stability but also contributes to the aesthetics of the aircraft. The GPS module mounting bracket 44 is cleverly integrated into the semi-elliptical nose cone on the top of the aircraft. This bracket features a special anti-reverse connection notch to ensure the GPS module is not connected incorrectly during installation, thus preventing equipment damage or performance degradation due to operational errors. More importantly, this semi-elliptical nose cone design is not only aesthetically pleasing but also highly functional. It effectively reduces wind resistance during flight, improving the aircraft's aerodynamic performance. Simultaneously, during catapult launch, this design effectively absorbs and disperses impact energy, protecting the aircraft from damage. Furthermore, the battery compartment design makes full use of available space for battery transfer, improving space utilization and ensuring the aircraft's center of gravity is centrally located; this design effectively avoids a nose-heavy problem, thereby improving flight stability and safety.

[0058] Furthermore, the arm support mounting base 34 is provided with a first opening slot arranged at intervals along the circumferential direction to provide space for the arm 8 to rotate, while ensuring that there is a gap between the arm 8 and the arm support mounting top 30 in the folded state. The base mounting plate 40 is provided with a second opening slot 32 and a third opening slot 33 arranged at intervals along the circumferential direction. The second opening slot 32 provides space for the landing gear 36 to rotate, and the third opening slot 33 provides space for the lower end of the flight rotor module 1 to be stored.

[0059] For the first takeoff mode, the working principle is described below based on flight tests:

[0060] For takeoff from the ground, first power on the aircraft and select the PosHold flight mode using the remote controller stick. Wait for the flight controller to perform a self-check and satellite positioning. Once enough satellites have been received, unlock the flight controller with the remote controller, and the aircraft motors will maintain idle speed. Pushing the remote controller stick increases the motor speed, and the aircraft will take off with the assistance of the flight controller. During flight, the remote controller stick controls the aircraft's pitch and roll angles, yaw rate, and ascent and descent speeds. When the stick is released, the aircraft will maintain its current three-dimensional position (including horizontal and vertical altitude) under the guidance of BeiDou satellites. In windy conditions, the aircraft will automatically hover against the wind. For return flight, move the remote controller stick to the return-to-home position. The aircraft will automatically ascend to the preset return-to-home altitude, fly back to the takeoff position under BeiDou satellite navigation, and land automatically.

[0061] The following is a description of an embodiment of the second takeoff mode:

[0062] Example 2: It is basically the same as Example 1, except that when the aircraft adopts the second takeoff mode, the initial state of the flight rotor module 1 is the first folded state, and the initial state of the landing gear 36 is the second folded state.

[0063] For the second takeoff mode (catapult takeoff), the working principle is described below based on flight tests:

[0064] First, the arms and landing gear of the multi-takeoff mode aircraft are manually folded and placed inside the launch device (such as an ejection tube). The flight controller is then set to Throw mode using a remote control joystick pre-selected on a laptop. Under external force, the aircraft ejects from the launch device. At the instant of ejection, the wing folding switching module 2 passively deploys the flight rotor module 1, and the landing gear also switches to the deployed state. The aircraft's status is then detected by the IMU sensor in the flight controller. When the aircraft reaches its highest point, the flight controller intervenes to control it. Based on feedback from the IMU sensor, the attitude and altitude controllers within the flight controller adjust the aircraft's attitude and altitude, ultimately hovering the aircraft at the pre-designed altitude. Furthermore, the aircraft can be controlled using a remote control or by using a pre-programmed sequence to complete pre-set tasks. Optionally, the flight controller model is NxtPx4.

[0065] The specific embodiments of the present invention have been described in detail above with reference to the accompanying drawings. However, the present invention is not limited to the above embodiments. Within the scope of knowledge possessed by those skilled in the art, various changes can be made without departing from the spirit of the present invention.

Claims

1. A multi-takeoff mode aircraft, characterized in that, The aircraft includes a flight rotor module (1), a wing folding and switching module (2), a connecting module (3), a support module (4), a landing gear folding and switching module (5), a base fixing module (6), a nose module (7), and landing gear (36). The nose module (7), the connecting module (3), the support module (4), and the base fixing module (6) are arranged sequentially along the axial direction of the aircraft. The wing folding and switching module (2) is connected to the connecting module (3) and the nose module (7). By cooperating with the flight rotor module (1) and the wing folding and switching module (2), the flight rotor module (1) has a first deployed state and a first folded state. The landing gear folding switching module (5) is connected to the connecting module (3), the bracket module (4), and the base fixing module (6). By cooperating with the landing gear folding switching module (5), the landing gear (36) has a second deployed state and a second folded state. When the aircraft adopts the first take-off mode, the initial state of the flight rotor module (1) is the first deployed state, and the initial state of the landing gear (36) is the second deployed state. When the aircraft adopts the second take-off mode, the initial state of the flight rotor module (1) is the first folded state, and the initial state of the landing gear (36) is the second folded state. The wing folding switching module (2) includes a first bolt (15), a first bolt fixing nut (16), a double torsion spring (17), and an arm bracket (31). The first bolt (15) passes through the first arm bracket (31), one side of the double torsion spring (17), the arm (8) of the flight rotor module (1), the other side of the double torsion spring (17), and the second arm bracket (31) from one end to the other end, and is then fixed by the first bolt fixing nut (16). The arm brackets (31) are arranged on opposite sides along the axial direction of the aircraft to connect the nose module (7) and the connecting module (3). An extension (9) is provided on the side of the two arm brackets (31) facing each other. The extension (9) is provided with a first through hole (10) for the end of the double torsion spring (17) to extend into. A slot is provided on the outside of the arm (8) for fixing the double torsion spring (17). The connection module (3) includes a boom support fixing base (34) and a lower half of the battery compartment (35); the boom support fixing base (34) is connected to the landing gear bracket (39) in the landing gear folding switching module (5) through a fixing member, and is connected to one side of the boom support (31) in the wing folding switching module (2) through a fixing member; the lower half of the battery compartment (35) is attached to the boom support fixing base (34) on the side near the nose module (7); The landing gear folding switching module (5) includes a single torsion spring (20), a second bolt (18), a second bolt fixing nut (19), and a landing gear bracket (39). The top of the landing gear bracket (39) is connected to the arm bracket fixing base (34) in the connecting module (3), the middle is connected to the bracket module (4), and the bottom is connected to the base fixing module (6). The second bolt (18) passes through the through hole on one side of the landing gear bracket (39) away from the nose module (7), the through hole on one side of the landing gear (36), the single torsion spring (20), the through hole on the other side of the landing gear (36), and the through hole on the other side of the landing gear bracket (39) away from the nose module (7) before being fixed by the second bolt fixing nut (19). The landing gear bracket (39) is provided with a second through hole (23) for connecting the bracket module (4), a third through hole (24) for fixing one end of the single torsion spring (20), a buried hole (25) for embedding and fixing the hot melt nut, a baffle (26) for limiting the landing gear (36), a limiting tenon (27) for cooperating with the base fixing module (6), and a screw hole (28) for connecting with the arm bracket fixing base (34). The bracket module (4) and the landing gear bracket (39) are connected by bolts (21) passing through the fourth through hole (29) of the bracket module (4) and the second through hole (23) of the landing gear bracket (39) and by nuts (22); the bracket module (4) is used to install the flight controller; One end of the single torsion spring (20) is connected to the third through hole (24) of the landing gear bracket (39), and the other end of the third through hole (24) is connected to the through hole of the landing gear (36); The landing gear bracket (39) and the base fixing module (6) are fixed by the limiting tenon (27) engaging with the limiting hole (42) of the base fixing module (6) and then by heating and fixing the hot melt nut on the landing gear bracket (39).

2. The multi-takeoff mode aircraft according to claim 1, characterized in that, The number of the flight rotor module (1), wing folding switching module (2), landing gear folding switching module (5), and landing gear (36) are equal, and multiple modules are provided.

3. The multi-takeoff mode aircraft according to claim 1, characterized in that, The flight rotor module (1) includes an arm (8), a DC motor (11), a folding propeller (12), a DC motor mounting bracket (13), and a folding propeller mounting bracket (14). One end of the DC motor (11) is equipped with a folding propeller (12) through the folding propeller mounting bracket (14), and the other end of the DC motor (11) is fixed to one end of the arm (8) through the DC motor mounting bracket (13). The other end of the arm (8) cooperates with the wing folding switching module (2).

4. The multi-takeoff mode aircraft according to claim 1, characterized in that, The base fixing module (6) includes a base fixing plate (40), and the base fixing plate (40) has a limiting hole (42) that cooperates with the landing gear bracket (39) in the landing gear folding switching module (5).

5. The multi-takeoff mode aircraft according to claim 1, characterized in that, The head module (7) includes a boom support fixing top seat (30), a cone cover (43), a GPS module fixing seat (44), and an upper part of the battery compartment (45). The non-point tip of the cone cover (43) is connected to the boom support fixing top seat (30). The upper part of the battery compartment (45) is provided on the side of the boom support fixing top seat (30) facing the cone cover (43). The upper part of the battery compartment (45) is combined with the lower part of the battery compartment (35) in the connecting module (3) to form a complete battery compartment. The GPS module fixing seat (44) is built into the cone cover (43) and covers the upper part of the battery compartment (45).

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