Connecting device and split type aircraft

Abstract

The invention discloses a connecting device and a split type aircraft, the connecting device is used for connecting a flight assembly and a cabin, and relates to the technical field of aircrafts, the connecting device comprises a first connecting piece connected with the flight assembly and a second connecting piece connected with the cabin, the first connecting piece is provided with a guide section and a sliding section, the guide section is connected with the sliding section, and the second connecting piece is connected with the cabin. The first connecting piece and the second connecting piece are used for connecting the flight assembly with the cabin; the second connecting piece is in sliding connection with the first connecting piece, and the guide part of the second connecting piece is rotationally connected with the second connecting piece; the guide part is located at the end, close to the first connecting piece, of the second connecting piece when the second connecting piece is in butt joint, and the guide section is used for guiding the second connecting piece so that the guide part can be slidably connected with the sliding section. The technical scheme provided by the invention can be used for quickly assembling and separating the cabin and the flight assembly of the split type electric vertical take-off and landing aircraft on the ground, and the problems that a connecting structure and bearing stress are relatively complex, and butt joint is inaccurate during assembling are solved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a connecting device and a split-type aircraft. Background Art

[0002] In recent years, with the continuous development of urban air transportation configuration, electric vertical take-off and landing (eVTOL) aircraft has attracted more and more attention. Manned safety is the minimum requirement for the opening of low-altitude urban areas, and it is also an important factor that must be considered in the design of electric vertical take-off and landing aircraft.

[0003] Traditional aircraft usually design the flight component and the cockpit as an inseparable whole. In order to make the aircraft have multi-purpose operation functions and protect the passengers and pilots in the cockpit, the split electric vertical take-off and landing aircraft of the present invention designs the flight component and the cockpit as a detachable structure. When the aircraft lands, the cockpit and the flight component are separated into independent carriers with land operation and air flight functions respectively; when the aircraft fails in flight, the cockpit and the flight component can be separated and then the parachute set on the cockpit is opened to make the cockpit land safely and smoothly. In the related art, the connection structure between the cockpit and the flight component is relatively complicated, and there is a problem of inaccurate docking during assembly. Summary of the invention

[0004] The main purpose of the present invention is to propose a connecting device and a split aircraft, aiming to solve the problems of complex connection structure between the cockpit and flight components of a split vertical take-off and landing aircraft, inaccurate docking during rapid assembly, and locking and bearing capacity problems after connection.

[0005] To achieve the above-mentioned purpose, the connecting device proposed in the present invention is used to connect a flight component and a cockpit, including: a first connecting member and a second connecting member, the first connecting member having a guide section and a sliding section, the guide section is connected to the sliding section, and the first connecting member is used to connect the flight component; the second connecting member is slidably connected to the first connecting member, the second connecting member includes a guide portion, and the guide portion is rotatably connected to the second connecting member; the guide portion is located at one end of the second connecting member close to the first connecting member, and the second connecting member is used to connect the cockpit; wherein the guide section is used to guide the second connecting member so that the guide portion is slidably connected to the sliding section.

[0006] In one embodiment, the guide portion includes at least two guide wheels, the guide section includes two guide grooves, and the two guide wheels are located on opposite sides of the two guide grooves, so that the second connecting member is correspondingly slidably connected to the first connecting member.

[0007] In one embodiment, the sliding section includes a sliding groove, the guide wheel is slidably disposed in the sliding groove, and the outer peripheral wall of the guide wheel abuts against the side wall of the sliding groove.

[0008] In one embodiment, the distance between the two guide grooves gradually decreases in a direction from the guide grooves away from the sliding groove.

[0009] In one embodiment, the second connecting member further includes a load-bearing wheel, which abuts against the upper and lower walls of the sliding groove to bear the vertical load, and the load-bearing wheel is located on a side of the second connecting member facing the first connecting member.

[0010] In one embodiment, the second connecting member includes a locking device, and the first connecting member is provided with an insertion hole, and the locking device can be inserted into the insertion hole to lock the first connecting member and the second connecting member.

[0011] The present invention also proposes a split aircraft, comprising: a connecting device, a flying component and a cockpit, wherein the flying component is connected to the first connecting member, and the flying component is located on the side of the first connecting member facing away from the second connecting member; the cockpit is connected to the second connecting member, and the cockpit is located on the side of the second connecting member facing away from the first connecting member; the first connecting member is slidably connected to the second connecting member to connect or separate the cockpit from the flying component.

[0012] In one embodiment, the flying assembly includes folding wings and a folding assembly, and the folding assembly is used to fold the folding wings along the direction of the cabin, so that the flying assembly can adjust the height and be stably placed when the cabin is assembled and separated from the flying assembly.

[0013] In one embodiment, the flying assembly further comprises a forward-tilted rotor and a drive locking assembly, wherein the forward-tilted rotor is rotationally connected to the flying assembly, and the drive locking assembly is used to drive the forward-tilted rotor to rotate around its rotation axis and lock the forward-tilted rotor at a predetermined rotation angle.

[0014] In one embodiment, the flight component further includes a tail rudder and a rear propeller, wherein the tail rudder is rotationally connected to the flight component, and the rear propeller is rotationally connected to the flight component.

[0015] The technical solution of the present invention is to design a connection device for a split aircraft, which is intended to simplify the docking and separation process between the cabin carrier and the aircraft carrier and to make it accurate and reliable. The connection device is composed of a first connection member and a second connection member, the first connection member includes a guide section and a sliding section, wherein the guide section is designed to guide the second connection member to dock accurately and quickly. The second connection member is equipped with a guide portion, which is rotatably connected to the second connection member and is located at one end of the second connection member close to the first connection member. During the docking process, the folding wing adjusts the height of the first connection member, and the guide section guides the left and right directions of the second connection member, so that the guide portion and the sliding section are smoothly slid and connected, thereby achieving accurate docking between the cabin carrier and the aircraft carrier. This design improves the accuracy and reliability of the connection and reduces the potential safety risks caused by inaccurate docking. Through the cooperation of the guide section and the guide portion, it can be ensured that the cabin carrier and the aircraft carrier can be quickly and accurately connected or separated even in complex or emergency situations. In addition, this design may also simplify the manufacturing and maintenance process because it reduces the required complex mechanical structure, thereby reducing costs and improving the reliability of the entire system. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0017] Figure 1 A schematic structural diagram of an embodiment of a first connecting member provided by the present invention;

[0018] Figure 2 A schematic structural diagram of an embodiment of a second connecting member provided by the present invention;

[0019] Figure 3 A schematic side view of the structure of an embodiment of a split-type aircraft provided by the present invention;

[0020] Figure 4 A schematic top view of the structure of another embodiment of the split aircraft provided by the present invention;

[0021] Figure 5 The present invention is a schematic structural side view of another embodiment of the split aircraft provided by the present invention.

[0022] Description of Figure Numbers:

[0023] 100. Connecting device; 1. First connecting member; 11. Sliding section; 11a. Sliding groove; 11b. Locking hole; 12. Guide section; 12a. Guide groove; 13. Limit block; 2. Second connecting member; 21. Guide section; 211. Guide wheel; 22. Load-bearing wheel; 23. Locking device; 200. Split-type aircraft; 3. Flight assembly; 4. Cockpit; 31. Folding wing; 32. Folding assembly; 33. Forward tilt rotor; 34. Tilt drive assembly; 35. Steering rudder; 36. Rear rotor.

[0024] The realization of the purpose, functional features and advantages of the present invention will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0025] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0026] It should be noted that if the embodiments of the present invention involve directional indications (such as up, down, left, right, front, back, etc.), the directional indications are only used to explain the relative position relationship, movement status, etc. between the components in a certain specific posture. If the specific posture changes, the directional indication will also change accordingly.

[0027] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the present invention, the descriptions of "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of technical features indicated. Therefore, the features limited to "first" and "second" may explicitly or implicitly include at least one of the features. In addition, if "and / or" or "and / or" appears in the full text, its meaning includes three parallel solutions. Taking "A and / or B" as an example, it includes solution A, solution B, or solutions that satisfy both A and B. In addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on the ability of ordinary technicians in this field to implement. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0028] The present invention provides a connecting device 100 .

[0029] See also Figure 1 and Figure 2In one embodiment of the present invention, the connecting device 100 is used to connect the flight component 3 and the cabin 4. The connecting device 100 includes a first connecting member 1 and a second connecting member 2. The first connecting member 1 has a sliding section 11 and a guide section 12. The sliding section 11 is connected to the guide section 12. The first connecting member 1 is used to connect the flight component 3; the second connecting member 2 is slidably connected to the first connecting member 1, and the second connecting member 2 includes a guide portion 21. The guide portion 21 is rotatably connected to the second connecting member 2; the guide portion 21 is located at one end of the second connecting member 2 close to the first connecting member 1, and the second connecting member 2 is used to connect the cabin 4; wherein the guide section 12 is used to guide the second connecting member 2 so that the guide portion 21 guides the load-bearing wheel 22 to slide into the sliding section 11 for connection.

[0030] In one embodiment, in the design of the vertical take-off and landing split aircraft 200, the first connector 1 is a key component connecting the flight assembly 3 and the cockpit 4. The first connector 1 is connected to the flight assembly 3 by bolts or riveting. The first connector 1 ensures that the cockpit 4 and the flight assembly 3 can be effectively and accurately docked and separated during ground assembly, or the cockpit 4 and the flight assembly 3 can be quickly separated and landed by parachute in an emergency during flight, so as to ensure the safety of passengers and drivers. Specifically, the first connector 1 includes a guide section 12 and a sliding section 11. The guide section 12 is mainly used to guide the docking of the second connector 2 and the first connector 1. The sliding section 11 is connected to the second connector 2 after docking and is used for bearing in flight; generally, the sliding connection is made by a guide rail and a pulley structure. The design of the first connector 1 and the second connector 2 needs to ensure sufficient strength and durability to withstand various loads during flight, and also ensure that they can be quickly and reliably separated in an emergency. The material selection of the first connector 1 usually needs to meet the requirements of high strength, light weight and corrosion resistance. Generally speaking, aluminum alloy or carbon fiber composite materials can be used. These materials have the characteristics of light weight and high strength, and are very suitable for the manufacture of the first connector 1 and the second connector 2. Not only can the weight of the split aircraft 200 be reduced, but the strength and durability of the structure in extreme environments can also be ensured. In an emergency, the cockpit 4 and the flight component 3 can be separated quickly and reliably to ensure the safety of passengers and pilots. During normal flight, the connection between the first connector 1 and the second connector 2 needs to maintain stability and reliability to prevent accidental separation. During normal docking, the first connector 1 can be used as a guide rail for docking between the cockpit 4 and the flight component 3.

[0031] In this embodiment, the second connector 2 is a key component for realizing reliable connection and rapid separation of the cockpit 4 and the flight assembly 3. The second connector 2 is connected to the cockpit 4 by bolts or rivets; the second connector 2 is slidably connected and locked with the first connector 1 by a guide rail and a pulley structure, and the second connector 2 is designed to include a guide portion 21, which is rotatably connected with the second connector 2 to guide the second connector 2 to dock with the first connector 1 intactly. The guide portion 21 is located at one end of the second connector 2 close to the first connector 1. This design allows the sliding section 11 of the second connector 2 and the first connector 1 to be unlocked and slide backward relative to each other when the split aircraft 200 fails or other emergency situations occur, such as when the aircraft loses power or the battery explodes, so as to realize the rapid separation of the cockpit 4 from the flight assembly 3, and by quickly deploying a safe landing system, such as a parachute, the cockpit 4 is separated from the flight assembly 3 and lands safely, ensuring the safety of passengers in the cockpit 4 while maintaining the structural integrity and impact resistance of the cockpit 4. In the case of normal landing of the split aircraft 200, the first connector 1 and the second connector 2 can be unlocked to disassemble the separated cockpit 4, so as to facilitate the inspection and maintenance of the flight component 3 and the cockpit 4 respectively, and the cockpit 4 can also be operated or transported independently on the ground. The flight component 3 can be used as a shared flight carrier to mount other cockpits for flight or to mount cargo as a drone for independent flight. The material selection of the second connector 2 usually needs to meet the requirements of high strength, light weight and corrosion resistance. Generally speaking, aluminum alloy or carbon fiber composite materials can be used. These materials have the characteristics of light weight and high strength, and are very suitable for the manufacture of the second connector 2. It can not only reduce the weight of the split aircraft 200, improve performance and range, but also ensure reliability and durability in extreme environments. In addition, considering that the second connector 2 needs to withstand greater stress, some high-strength metal materials, such as stainless steel or titanium alloy, may also be used to manufacture key connectors. During normal flight, the first connecting member 1 and the second connecting member 2 need to maintain the stability and reliability of the connection to prevent accidental separation. In an emergency, the cockpit 4 and the flight component 3 can be separated quickly and reliably, and a parachute can be used for safe landing to ensure the safety of passengers and pilots.

[0032] The technical solution of the present invention is to design a connection device 100 for a split aircraft 200, which is intended to simplify and improve the reliability of the docking and separation process between the cabin 4 carrier and the split aircraft 200 carrier. The connection device 100 is composed of a first connector 1 and a second connector 2, wherein the first connector 1 includes a sliding section 11 and a guide section 12, wherein the guide section 12 is designed to guide the second connector 2 to dock correctly. The second connector 2 is equipped with a guide portion 21, which is rotatably connected to the second connector 2 and is located at one end of the second connector 2 close to the first connector 1 during docking. During the docking process, the guide section 11 guides the second connector 2, so that after the guide portion 21 docks with the guide section 12, the load-bearing wheel 22 is guided to slide and connect smoothly with the sliding section 11, thereby achieving accurate docking between the cabin 4 carrier and the split aircraft 200 carrier. This design improves the accuracy and reliability of the connection and reduces the potential safety risks caused by inaccurate docking. The cooperation of the guide section 12 and the guide portion 21 can ensure that the cockpit 4 carrier and the split aircraft 200 carrier can be quickly and accurately connected or separated even in complex or emergency situations. In addition, this design can also enable the cockpit 4 carrier and the split aircraft 200 carrier to independently operate on the ground and fly in the air after separation, and facilitate transportation and maintenance because it reduces the required complex mechanical structure, thereby reducing costs and improving the reliability of the entire system.

[0033] In one embodiment of the present invention, see Figure 2 The guide portion 21 includes at least two guide wheels 211, and the guide section 12 includes two guide grooves 12a. When docking, the two guide wheels 211 are located on opposite sides of the two guide grooves 12a, so that the second connecting member 2 is correspondingly slidably connected to the first connecting member 1.

[0034] In one embodiment of the present invention, the guide portion 21 of the second connector 2 is provided with at least two guide wheels 211, and the guide section 12 of the first connector 1 is provided with two corresponding guide grooves 12a. The two guide wheels 211 are respectively installed on both sides of the second connector 2, and correspond to the guide groove 12a of the first connector 1. Under this configuration, when the second connector 2 needs to be slidably connected with the first connector 1, the guide wheel 211 will first be inserted into the guide groove 12a to ensure that the second connector 2 can be smoothly slid along the trajectory of the guide groove 12a and pushed into the sliding groove 11a of the sliding section 11. This design can ensure an accurate and reliable connection between the first connector 1 and the second connector 2, provide a stable connection during normal flight and maintenance, and quickly slide and separate and disconnect the cockpit 4 from the flight assembly 3 in an emergency.

[0035] In one embodiment of the present invention, see Figure 1The sliding section 11 of the first connecting member 1 includes a sliding groove 11a, and the guide section 12 includes a guide groove 12a. The distance between the two guide sections 12 gradually decreases in the direction in which the guide section 12 faces away from the sliding section 11. In addition, a limiting block 13 is installed on the side of the sliding groove 11a away from the guide section 12. This design allows the guide wheel 211 on the second connecting member 2 to accurately guide the guide wheel 211 and the load-bearing wheel 22 into the sliding groove 11a after moving along the guide groove 12a, thereby realizing a continuous sliding connection between the guide wheel 211 and the sliding groove 11a. When the guide wheel 211 hits the limiting block 13, the second connecting member 2 stops sliding, and the connection between the first connecting member 1 and the second connecting member 2 is fixedly locked by the locking device 23.

[0036] In one embodiment, the sliding section 11 and the guide section 12 may be made of high-strength wear-resistant materials, such as aluminum alloy or carbon fiber reinforced composite materials, to ensure that their shape and function are maintained during long-term use. At the same time, the surfaces of the sliding groove 11a and the guide groove 12a may be specially treated, such as adding a lubricating coating, to reduce friction and wear and ensure long-term reliable operation. This design not only improves the practicality and reliability of the connecting device 100, but also simplifies the assembly process because it reduces the number of parts that need to be locked or adjusted separately. Through this design, the connection device 100 of the split aircraft 200 can be improved in terms of ease of operation and ease of maintenance when implementing connection assembly and separation.

[0037] In one embodiment of the present invention, see Figure 2 The second connecting member 2 includes a guide wheel 211 and a load-bearing wheel 22. The guide wheel 211 is installed at one end of the guide section 12 close to the first connecting member 1, and the load-bearing wheel 22 is distributed along the length direction of both sides of the second connecting member 2. The guide wheel 211 is a key component of the guide portion 21 of the second connecting member 2, and the load-bearing wheel 22 is a key component for the second connecting member to be firmly connected and bear the load with the first connecting member. This design enables the second connecting member 2 to be quickly and accurately docked with the first connecting member 1 and ensures that the structural load-bearing force is evenly distributed and the connection is reliable.

[0038] In this embodiment, the materials and sizes of the guide wheel 211 and the load-bearing wheel 22 are carefully selected and designed to meet the requirements of strength and durability. The guide wheel 211 and the load-bearing wheel 22 can be made of high-strength and high-toughness wear-resistant materials, such as hard rubber or nylon reinforced engineering plastics. Generally speaking, the guide wheel 211 and the load-bearing wheel 22 can be rollers or balls. During the connection process, the outer peripheral wall of the guide wheel 211 is in direct contact with the side walls of the guide groove 12a and the sliding groove 11a in turn, and the outer peripheral wall of the load-bearing wheel 22 is in direct contact with the upper and lower walls of the sliding groove 11a, so that the second connecting member 2 can be smoothly linearly moved along the sliding groove 11a of the first connecting member through the guide wheel 211 and the load-bearing wheel 22 to the locking position of the abutment limit block 13, preventing the second connecting member 2 from moving forward relative to the first connecting member 1, and connecting the first connecting member 1 and the second connecting member 2 as a whole through the locking device 23. The guide wheel 211 is constructed so that it can abut against the side wall of the sliding groove 11a of the first connecting member 1, and the bearing wheel 22 is constructed so that it can physically abut against the upper and lower walls of the sliding groove 11a of the first connecting member 1, thereby providing necessary guidance and support when the second connecting member 2 moves along the sliding groove 11a. This design helps the stability of the connection device 100, maintains the stability of the connection when the split aircraft 200 encounters bumps or vibrations, and plays a vibration reduction role. In addition, when the cockpit 4 needs to be quickly separated from the flight component 3 in an emergency situation during flight, the guide wheel 211 and the bearing wheel 22 can quickly move along the sliding groove 11a to the guide groove 12a after being unlocked by the locking device 23. During the sliding separation process, the guide wheel 211 and the bearing wheel 22 in the sliding grooves 11a on both sides can reduce the swing or unstable movement of the cockpit 4, ensuring that the cockpit 4 can be smoothly and quickly separated from the flight component 3 and landed by parachute, ensuring the safe landing of the passengers in the cockpit 4.

[0039] In one embodiment of the present invention, see Figure 2 The second connecting member 2 includes a locking device 23, and a socket 11b is provided on the first connecting member 1. When the second connecting member 2 moves along the sliding groove 11a to the locking position abutting the limit block 13, the locking device 23 can be inserted into the socket 11b to complete the docking and lock the first connecting member 1 and the second connecting member 2 into a whole.

[0040] In one embodiment, the second connecting member 2 is equipped with a locking device 23, which is designed to match the socket 11b on the first connecting member 1. Specifically, the spacing between the locking device 23 and the guide wheel 211 of the second connecting member 2 matches the spacing between the upper limit block 13 and the socket 11b of the first connecting member 1, and the telescopic latch of the locking device 23 has a structure that matches the shape and size of the socket 11b of the first connecting member 1, so that when the guide wheel 211 of the second connecting member 2 slides along the sliding groove 11a of the first connecting member 1 to the stop block 13, the telescopic latch of the locking device 23 can be smoothly inserted and fixed in the socket 11b. Once the telescopic latch of the locking device 23 is fully inserted into the socket 11b, it will prevent the second connecting member 2 from moving along the sliding groove 11a of the first connecting member 1, thereby achieving the locking of the first connecting member 1 and the second connecting member 2. This locking mechanism ensures that the connection between the cockpit 4 and the flight assembly 3 is stable under normal operating conditions to prevent accidental separation, and the two connecting parts are unlocked and separated only when necessary by operating the locking device 23. The design of the locking device 23 and the socket 11b takes into account the simplicity and safety of operation, so as to facilitate quick unlocking in an emergency.

[0041] The present invention also proposes a split aircraft 200, which includes a connecting device 100, a flight component 3 and a cockpit 4. The specific structure of the connecting device 100 refers to the above embodiment. Since the split aircraft 200 adopts all the technical solutions of all the above embodiments, it at least has all the beneficial effects brought by the technical solutions of the above embodiments, which will not be repeated here. Among them, the flight component 3 is connected to the first connecting member 1, and the flight component 3 is located on the side of the first connecting member 1 facing away from the second connecting member 2; the cockpit 4 is connected to the second connecting member 2, and the cockpit 4 is located on the side of the second connecting member 2 facing away from the first connecting member 1; the first connecting member 1 is slidably connected to the second connecting member 2 to connect or separate the cockpit 4 from the flight component 3.

[0042] In the present embodiment, the split aircraft 200 includes a connecting device 100, which can enable the cockpit 4 to be quickly connected and separated from the flight assembly 3. Specifically, the first connecting member 1 is connected to the flight assembly 3 by bolts or rivets, the flight assembly 3 is located above the first connecting member 1, and the cockpit 4 is located below the second connecting member 2, and the flight assembly 3 is connected to the cockpit 4 by the sliding connection between the second connecting member 2 and the first connecting member 1. A sliding connection mechanism is adopted between the first connecting member 1 and the second connecting member 2, so that the cockpit 4 can be conveniently connected to the flight assembly 3 or quickly separated when necessary. This design allows the cockpit 4 to be quickly disconnected from the flight assembly 3 in an emergency, such as when an irreparable failure occurs in the split aircraft 200, and a safe landing is achieved through a safety system (such as a parachute), thereby ensuring the safety of passengers and crew members. At the same time, during ground operations, the connecting device 100 also facilitates the independent operation, transportation and maintenance of the cockpit 4 and the flight component 3 of the split aircraft 200 after separation, thereby improving the availability and economy of the split aircraft 200 in a wider range of application scenarios.

[0043] In one embodiment of the present invention, see Figure 5 The flying assembly 3 includes folding wings 31 and a folding assembly 32. The folding assembly 32 is used to fold the folding wings 31 along the direction of the cabin 4 so that the flying assembly 3 can be stably placed when the cabin 4 is separated from the flying assembly 3.

[0044] In one embodiment, the folding assembly 32 of the split aircraft 200 is used to fold the folding wing 31 along the direction of the cabin 4, so that when the cabin 4 is separated from the flight assembly 3, the flight assembly 3 can adjust the height relative to the cabin 4 and be stably placed. Specifically, the flight assembly 3 of the split aircraft 200 includes a folding wing 31 and a folding assembly 32, wherein the folding assembly 32 is responsible for controlling the movement of the folding wing 31. When the cabin 4 needs to be separated from the flight assembly 3, the folding wing 31 will fold along the direction of the cabin 4, which is achieved by the mechanism of the folding assembly 32. The design of the folding wing 31 plays a supporting role during the separation process, so that the flight assembly 3 can be stably placed, thereby ensuring that the cabin 4 can be safely separated from the flight assembly 3, and the flight assembly 3 will not roll or unstable movement after separation. This design improves the stability and safety of the split aircraft 200 after landing, and allows the flight assembly 3 and the cabin 4 to be safely stored or recovered after separation.

[0045] In one embodiment of the present invention, see Figure 4 and Figure 5The flight assembly 3 also includes a forward tilt rotor 33 and a tilt drive assembly 34. The forward tilt rotor 33 is rotatably connected to the first connecting member 1 of the flight assembly 3. The tilt drive assembly 34 has a self-locking function for driving the rotation of the forward tilt rotor 33 and locking the forward tilt rotor 33 at a desired rotation angle.

[0046] In this embodiment, the flight assembly 3 of the split aircraft 200 includes a forward tilting wing 33 and a tilting drive assembly 34, wherein the forward tilting wing 33 is combined with the first connecting member 1 of the flight assembly 3 by a rotational connection. The function of the tilting drive assembly 34 is to drive the forward tilting wing 33 to rotate and lock at any angle during flight to ensure the aerodynamic performance and flight stability of the split aircraft 200. Specifically, the forward tilting wing 33 is designed to rotate around its front beam axis to adjust the attitude angle of the split aircraft 200 and control the aerodynamic performance and maneuvering flight of the split aircraft 200 in different flight stages. This rotational connection can ensure that the forward tilting wing 33 changes its angle in different flight modes such as take-off, cruising and landing to adapt to different flight requirements. The tilting drive assembly 34 includes a group of actuators and locking devices, such as a screw-type telescopic actuator, a locking pin, a locking bolt or other locking mechanism. When the split aircraft 200 needs to change the flight mode or perform maneuvers, the forward tilt rotor 33 can be rotated and locked at the required rotation angle by operating the tilt drive assembly 34. The operation of the tilt drive assembly 34 can be manual, or it can be achieved by automatic control methods such as electric, hydraulic or pneumatic. In the automatic control method, a drive device such as a motor, a hydraulic system or a pneumatic system, as well as corresponding control logic and feedback mechanisms may be involved to achieve accurate and reliable locking and unlocking operations. Through this design, the split aircraft 200 can utilize the aerodynamic lift-increasing effect of the forward tilt rotor 33 in different flight stages, while ensuring that the rotation angle of the forward tilt rotor 33 is accurately controlled during flight, thereby improving the flight performance and safety of the split aircraft 200.

[0047] In one embodiment of the present invention, see Figure 3 and Figure 4 The flight assembly 3 further includes a steering rudder 35 and a rear propeller 36 , wherein the steering rudder 35 is rotationally connected to the flight assembly 3 , and the rear propeller 36 is rotationally connected to the flight assembly 3 .

[0048] In this embodiment, the flight assembly 3 of the split aircraft 200 includes a steering rudder 35 and a rear propeller 36, the steering rudder 35 is rotationally connected to the flight assembly 3, and the rear propeller 36 is rotationally connected to the flight assembly 3. Specifically, the yaw motion of the split aircraft 200 in the vertical take-off and landing and hovering state can be controlled by controlling the deflection angle of the steering rudder 35. The design of the steering rudder 35 is usually located at the rear and lower part of the rear propeller 36, and the pressure difference and lateral force generated on the surface of the steering rudder 35 by the downward airflow when the rear propeller 36 rotates at high speed. The deflection angle of the steering rudder 35 is precisely controlled by the operation of the pilot or the command of the automatic control system to realize the steering of the split aircraft 200 as a whole in the vertical take-off and landing and hovering state. The design and layout of the rear propeller 36 are crucial to the stability and maneuverability of the split aircraft 200. The rotation connection between the rear propeller 36 and the flight assembly 3 provides the main thrust and attitude control of the split aircraft 200 in the vertical take-off and landing, hovering and flight process. In addition, the split aircraft 200 can accurately control the rotation angle of the forward tilting rotor 33 at different flight stages, thereby utilizing the aerodynamic lift-increasing advantage of the forward tilting rotor 33 to improve the flight performance and safety of the split aircraft 200. The combination of the steering rudder 35 and the rear propeller 36 further enhances the controllability and stability of the split aircraft 200 in the hovering state.

[0049] The above description is only an exemplary embodiment of the present invention, and does not limit the patent scope of the present invention. All equivalent structural changes made by using the contents of the present invention specification and drawings under the technical concept of the present invention, or directly / indirectly applied in other related technical fields are included in the patent protection scope of the present invention.

Claims

1. A connecting device for connecting a flight assembly (3) and a cockpit (4), characterized in that: include: A first connecting member (1), the first connecting member (1) having a guide section (12) and a sliding section (11), the guide section (12) being connected to the sliding section (11), the first connecting member (1) being used to connect the flying assembly (3); and a second connecting member (2), the second connecting member (2) being slidably connected to the first connecting member (1), the second connecting member (2) comprising a guide portion (21), the guide portion (21) being rotatably connected to the second connecting member (2); the guide portion (21) being located at one end of the second connecting member (2) close to the first connecting member (1), the second connecting member (2) being used for connecting to the cabin (4); The guide section (12) is used to guide the second connecting member (2) so that the guide portion (21) is finally slidably connected to the sliding section (11).

2. The connection device according to claim 1, characterized in that The guide portion (21) comprises at least two guide wheels (211), the guide section (12) comprises two guide grooves (12a), and the two guide wheels (211) are located on opposite sides of the two guide grooves (12a), so that the second connecting member (2) is correspondingly slidably connected to the first connecting member (1).

3. The connection device according to claim 2, characterized in that The sliding section (11) comprises a sliding groove (11a), the guide wheel (211) is slidably arranged in the sliding groove (11a), and the outer peripheral wall of the guide wheel (211) abuts against the bottom wall of the sliding groove (11a).

4. The connection device according to claim 3, characterized in that The distance between the two guide grooves (12a) gradually decreases in the direction of the guide groove (12a) facing away from the sliding groove (11a).

5. The connection device according to claim 3, characterized in that: The second connecting member (2) further comprises a load-bearing wheel (22), the load-bearing wheel (22) abutting against the side wall of the sliding groove (11a), and the load-bearing wheel (22) is located on the side of the second connecting member (2) facing the first connecting member (1).

6. The connection device according to any one of claims 1 to 5, characterized in that: The second connecting member (2) comprises a locking device (23); a plug hole (11b) is provided on the first connecting member (1); the locking device (23) can be inserted into the plug hole (11b) to lock the first connecting member (1) and the second connecting member (2).

7. A split-type aircraft, characterized in that: include: The connecting device according to any one of claims 1 to 6; a flying assembly (3), the flying assembly (3) being connected to the first connecting member (1), the flying assembly (3) being located on a side of the first connecting member (1) facing away from the second connecting member (2); and a cockpit (4), the cockpit (4) being connected to the second connecting member (2), the cockpit (4) being located on a side of the second connecting member (2) facing away from the first connecting member (1); The first connecting member (1) is slidably connected to the second connecting member (2) so as to connect or separate the cockpit (4) and the flight assembly (3).

8. The split-type aircraft according to claim 7, characterized in that: The flying assembly (3) comprises folding wings (31) and a folding assembly (32), wherein the folding assembly (32) is used to fold the folding wings (31) in the direction of the cabin (4), so that when the cabin (4) is separated from the flying assembly (3), the flying assembly (3) can adjust its height and be stably placed.

9. The split-type aircraft according to claim 7, characterized in that: The flight assembly (3) further comprises a forward tilting rotor (33) and a tilting drive assembly (34); the forward tilting rotor (33) is rotationally connected to the flight assembly (3); the tilting drive assembly (34) is used to drive the forward tilting rotor (33) to rotate and lock the rotation angle of the forward tilting rotor (33).

10. The split-type aircraft according to claim 7, characterized in that: The flight component (3) further comprises a tail rudder (35) and a rear propeller (36); the tail rudder (35) is rotationally connected to the flight component (3), and the rear propeller (36) is rotationally connected to the flight component (3).

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