Aircraft body quick release mechanism and aircraft

Abstract

The present application relates to the field of aircraft technology, in particular to a kind of aircraft body quick release mechanism and aircraft.The aircraft body quick release mechanism includes first body component, second body component and third body component, first body component is equipped with first front end hook;Second body component is equipped with second front end hook, and the second front end hook is overlapped with the first front end hook and is aligned to form front end hook;Third body component is equipped with front end hook slot, and the front end hook is movably installed in the front end hook slot, and the front end hook slot is installed with the locking device for the front end hook in the front end hook slot Locking and unlocking.The beneficial effects of the present application are: first body component, second body component and third body component can be quickly realized disassembly and assembly, simple and convenient operation, and disassembly and assembly efficiency is high.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft technology, in particular to an aircraft body quick release mechanism and an aircraft. BACKGROUND

[0002] With the development of the aircraft industry, especially industrial unmanned aerial vehicles, its application in map surveying, geological surveying, disaster monitoring, weather detection, air traffic control, border patrol monitoring, emergency rescue, logistics transportation, power inspection, agricultural plant protection, etc. is becoming more and more widely used. With more and more use scenarios, the performance requirements of unmanned aerial vehicles are also getting higher and higher. The current unmanned aerial vehicles can only meet the flight requirements, but it is very inconvenient for quick assembly, disassembly and storage, especially for emergency rescue, air traffic control, border patrol monitoring, map surveying, geological surveying, disaster monitoring, weather detection, air traffic control, etc. It is difficult to quickly complete assembly, replacement or disassembly and storage, which can easily cause serious consequences.

[0003] At present, although some schemes can realize the quick installation and disassembly between two body parts, the quick release of the two body parts is only suitable for small unmanned aerial vehicles, and the use scene is limited. Therefore, more and more use scenarios need to use three body parts to connect, but the quick assembly and disassembly operation of the three body parts is very inconvenient, especially in the same position to realize the quick assembly and disassembly of the three body parts, which is more difficult. SUMMARY

[0004] In view of the above-mentioned shortcomings of the prior art, the purpose of the present application is to provide an aircraft body quick release mechanism and an aircraft, which can solve the problem of difficult quick assembly and disassembly operation of three body parts in the same installation position in the prior art.

[0005] To achieve the above-mentioned purpose and other related purposes, the present application provides an aircraft body quick release mechanism, which comprises:

[0006] A first body part, the first body part is provided with a first front end hook;

[0007] A second body part, the second body part is provided with a second front end hook, the second front end hook and the first front end hook are overlapped and aligned to form a front end hook;

[0008] A third body part, the third body part is provided with a front end hook slot, the front end hook is movably installed in the front end hook slot, and the front end hook slot is provided with a locking device for locking and unlocking the front end hook in the front end hook slot.

[0009] Optionally, the first body component is provided with a first rear end hook, the second body component is provided with a second rear end hook, the second rear end hook is overlapped and aligned with the first rear end hook to form a rear end hook, the third body component is provided with a rear end hook slot, and the rear end hook and the rear end hook slot can be relatively moved along the X direction and hooked to be connected.

[0010] Optionally, the second body component is provided with a pin, and the first body component is provided with a pin hole for positioning the pin, the first body component and the second body component are assembled along the Y direction to make the first front end hook and the first rear end hook respectively overlapped and aligned with the second front end hook and the second rear end hook along the Y direction.

[0011] Optionally, the aircraft body quick release mechanism further comprises a first limiting structure, a second limiting structure and a third limiting structure, when the locking device locks the front end hook, the X direction gap, the Y direction gap and the Z direction gap between the first body component, the second body component and the third body component are respectively eliminated by the first limiting structure, the second limiting structure and the third limiting structure.

[0012] Optionally, the first body component and the second body component are provided with a lock mechanism, and the lock mechanism is used to lock the first body component and the second body component.

[0013] Optionally, the locking device comprises a mounting seat, a locking assembly and a driving assembly, the mounting seat is provided with a avoiding space for the front end hook to move along the X direction, the driving assembly is installed on the mounting seat and connected with the locking assembly, and the driving assembly drives the locking assembly to move along the Z direction to lock or unlock the front end hook.

[0014] Optionally, the locking assembly comprises a lock block and a connecting rod, the driving assembly is hinged with the lock block through the connecting rod, and the driving assembly drives the connecting rod to move to make the lock block move along the Z direction to press or release the front end hook in the avoiding space.

[0015] Optionally, the driving assembly comprises a driving piece and a sliding block, the sliding block is slidingly installed on the mounting seat and hinged with the connecting rod, and the driving piece drives the sliding block to slide to make the connecting rod move.

[0016] Optionally, the driving piece is a rotating handle, the rotating handle is rotationally installed on the mounting seat, the rotating handle penetrates through the sliding block and is threadedly connected with the sliding block, and the rotating handle rotates to drive the sliding block to move along the axis of the rotating handle.

[0017] To achieve the above and other related objectives, this application also provides an aircraft, including the quick-release mechanism for the aircraft fuselage as described above.

[0018] As described above, the quick-release mechanism for the aircraft body and the aircraft of the present invention have at least the following beneficial effects: they can quickly disassemble and assemble the first body component, the second body component and the third body component, and the operation is simple and convenient with high disassembly and assembly efficiency. Attached Figure Description

[0019] Figure 1 The diagram shown is a structural schematic of an embodiment of the quick-release mechanism for the aircraft body of the present invention.

[0020] Figure 2 Displayed as Figure 1 A structural diagram of the first, second, and third body components before assembly;

[0021] Figure 3 Displayed as Figure 1 Explosion diagrams of the first and second fuselage components;

[0022] Figure 4 Displayed as Figure 1 A structural schematic diagram of the first component of the machine body;

[0023] Figure 5 Displayed as Figure 1 A structural schematic diagram of the second body component;

[0024] Figure 6 Displayed as Figure 1 A structural diagram of the third body component;

[0025] Figure 7 Displayed as Figure 1 Top view of the quick-release mechanism of the aircraft fuselage;

[0026] Figure 8 Displayed as Figure 7 Sectional view of AA;

[0027] Figure 9 Displayed as Figure 7 Sectional view of BB;

[0028] Figure 10 Displayed as Figure 1 A schematic diagram of the structure when the front-end hook is in the unlocked state;

[0029] Figure 11 Displayed as Figure 1 Explosion diagram of the central locking device;

[0030] Figure 12 Displayed as Figure 1Structure diagram of the middle locking device in the unlocked state;

[0031] Figure 13 As shown in Figure 1 Structure diagram of the middle locking device in the locked state;

[0032] Figure 14 As shown in Figure 1 Explosion diagram of the middle locking device and the third machine body part.

[0033] Part number explanation

[0034] 100 - locking device; 101 - mounting seat; 1011 - limiting structure; 1012 - seat body; 1013 - support part; 1014 - guide groove; 1015 - avoiding space; 102 - locking assembly; 1021 - locking piece; 1022 - connecting rod; 103 - driving assembly; 1031 - driving piece; 1032 - sliding block; 1033 - limiting pin; 200 - first machine body part; 201 - first front hook; 202 - first rear hook; 203 - lock catch seat; 204 - pin hole; 300 - second machine body part; 301 - second front hook; 3011 - limiting part; 302 - second rear hook; 303 - lock catch; 304 - pin; 400 - third machine body part; 401 - front hook groove; 402 - rear hook groove; 403 - rear hook seat; 501 - first surface contact; 502 - second surface contact; 503 - third surface contact; 504 - fourth surface contact; 505 - fifth surface contact; 506 - sixth surface contact. DETAILED DESCRIPTION

[0035] The present application is described herein with reference to specific embodiments thereof which are illustrated in the attached drawings. These are intended to demonstrate, but not limit, the application. Other advantages and novel features of the present application will become apparent from the following detailed description, given by way of example only, when considered in conjunction with the accompanying drawings. Various modifications to the application will be readily apparent to those skilled in the art and the generic principles of the application can be applied to other applications without the use of the inventive faculty. Thus, the present application is not intended to be limited to the embodiments described herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

[0036] It is to be noted that the drawings provided in the present embodiment only schematically illustrate the basic concept of the present application, and only show the components related to the present application in the drawings, rather than being drawn according to the number, shape and size of the components in actual implementation. The shape, number and proportion of each component in actual implementation can be arbitrarily changed, and the layout pattern of the components can be more complex. The structure, proportion, size, etc. shown in the drawings attached to the present specification are only used to cooperate with the content disclosed in the specification, so as to be understood and read by those skilled in the art, and do not define the limiting conditions for the implementation of the present application, and therefore do not have substantial technical significance. Any modification of the structure, change of the proportional relationship or adjustment of the size, without affecting the effects and purposes that can be achieved by the present application, should still fall within the scope covered by the disclosed technical content of the present application. Meanwhile, the terms such as "upper", "lower", "left", "right", "middle" and "one" used in the present specification are only for the convenience of clear description, and are not used to limit the scope of the implementation of the present application. The change or adjustment of the relative relationship, without substantially changing the technical content, is also considered as the implementation scope of the present application.

[0037] Referring to Figure 1 and Figure 2Before the embodiments of the application are described in detail, the application environment of the application is described. The technology of the application is mainly applied to aircraft, especially to the quick disassembly and assembly of aircraft body parts, so that the aircraft body parts can be quickly installed and disassembled in various application scenarios, the installation is convenient, the interchangeability is high, and the disassembly and assembly efficiency is improved. For example, the third body part 400 can be a fuselage, a battery compartment, a fuel tank, a load compartment, a material compartment or other body parts; when the third body part 400 is a fuselage, after completing a work task once, the fuselage data needs to be downloaded or viewed online on the ground, and only the fuselage needs to be replaced to perform the next task, reducing the idle time of other parts; when the third body part 400 is a battery compartment or a fuel tank, after completing a work task once, the battery needs to be recharged or the fuel tank needs to be refueled, and only the battery compartment or the fuel tank needs to be replaced to perform the next task, reducing the idle time of other parts; when the third body part 400 is a load compartment, after completing a work task once, the load data needs to be downloaded or viewed online on the ground, and only the load compartment needs to be replaced to perform the next task, reducing the idle time of other parts, and in the case of consistent installation interfaces, different types of load compartments can be matched, so that one aircraft has multiple functions and multiple purposes, reducing the cost and cycle of developing new aircraft; when the third body part 400 is a material compartment, when the material is transported in one direction, the aircraft can return to perform the next task after the material compartment is disassembled (or the material compartment is dropped) at the destination; when the material is transported in both directions, the aircraft can return after the material compartment is disassembled and the material B is replaced after taking off and carrying the material A to the destination, realizing rapid material transportation. It can be seen that the aircraft body quick disassembly mechanism and the aircraft of the present application can realize the quick disassembly and interchange of various body parts in various application scenarios, and are simple, convenient and reliable.

[0038] Referring to Figures 1 to 6 In an embodiment, the application provides an aircraft body quick disassembly mechanism, comprising a first body part 200, a second body part 300 and a third body part 400. The first body part 200 is provided with a first front hook 201; the second body part 300 is provided with a second front hook 301, and the first front hook 201 and the second front hook 301 are overlapped and aligned to form a front hook; the third body part 400 is provided with a front hook slot 401, and the front hook is movably installed in the front hook slot 401, and the front hook slot 401 is provided with a locking device 100 for locking and unlocking the front hook in the front hook slot 401. The first front hook 201 and the second front hook 301 can be synchronously locked in the front hook slot 401 by the locking device 100, so that the first body part 200, the second body part 300 and the third body part 400 can be quickly unlocked or locked at the same position, the disassembly and assembly are simple and convenient, and the disassembly and assembly efficiency is improved.

[0039] Optionally, the first body part 200 and the second body part 300 are located above the third body part 400, the front hook is arranged at the bottom of the first body part 200 and the second body part 300, the front hook groove 401 is recessed at the top of the third body part 400, the front hook groove 401 comprises a first groove part and a second groove part, the locking device 100 is installed in the second groove part, the front hook enters the front hook groove 401 along the entrance of the first groove part, and then moves along the X direction to enter the second groove part and be locked in cooperation with the locking device 100. Wherein, the groove bottom depth of the second groove part is deeper than the groove bottom depth of the first groove part, so as to ensure the structural strength of the third body part 400 while providing sufficient movement space for the locking device 100.

[0040] Optionally, the locking device 100 can be fixedly installed in the front hook groove 401, wherein the locking device 100 is arranged in the front hook groove 401, and the locking device 100 can be fixedly connected with the third body part 400 through bolts, so that the connection is firm and stable, and the structure is reliable.

[0041] Referring to Figures 1 to 10 In an embodiment, the first body part 200 is provided with a first rear hook 202, the second body part 300 is provided with a second rear hook 302, the second rear hook 302 is overlapped and aligned with the first rear hook 202 to form a rear hook, the third body part 400 is provided with a rear hook groove 402, and the rear hook and the rear hook groove 402 can relatively move along the X direction and be hooked and connected. The front hook and the rear hook are respectively hooked and connected with the front hook groove 401 and the rear hook groove 402, so that the connection is more stable and reliable.

[0042] Optionally, the rear hook groove 402 is recessed at the top of the third body part 400, the rear hook seat 403 is installed in the rear hook groove 402, the rear hook extends into the rear hook groove 402 and moves along the X direction to be hooked with the rear hook seat 403, and the rear hook seat 403 limits the rear hook and the rear hook groove 402 from moving along the Z direction to be separated.

[0043] Optionally, the first body part 200 and the second body part 300 are distributed along the Y direction, the first front hook 201 and the first rear hook 202 are respectively arranged at the two ends of the bottom of the first body part 200, and the second front hook 301 and the second rear hook 302 are respectively arranged at the two ends of the bottom of the second body part 300. In addition, the first front hook 201 and the first rear hook 202 are arranged at the edges of the first body part 200 close to the second body part 300, and the second front hook 301 and the second rear hook 302 are arranged at the edges of the second body part 300 close to the first body part 200, so that when the first body part 200 and the second body part 300 are assembled in position, the first front hook 201 and the first rear hook 202 can be respectively overlapped and aligned with the second front hook 301 and the second rear hook 302.

[0044] Optionally, the front hook and the rear hook can be distributed along the X direction. The first body part 200 and the second body part 300 can be parts of a wing, for example, the first body part 200 is an inner wing, and the second body part 300 is an outer wing. In this application, the X direction can be the heading direction, the Y direction can be the span direction, and the Z direction can be the vertical direction, which is the vertical direction when the aircraft is flying horizontally.

[0045] Referring to Figures 1 to 10 In an embodiment, the second body part 300 is provided with a pin 304, and the first body part 200 is provided with a pin hole 204 for the insertion and positioning of the pin 304. The first body part 200 and the second body part 300 are assembled in position along the Y direction, so that the first front hook 201 and the first rear hook 202 are respectively overlapped and aligned with the second front hook 301 and the second rear hook 302 along the Y direction.

[0046] The pin 304 and the pin hole 204 are used to realize the positioning and assembly of the second body part 300 and the first body part 200. While ensuring the structural strength and direct force transmission, the positioning and installation are simple, suitable for batch processing, easy to ensure precision, high interchangeability, convenient to install, simple structure, low cost, and light weight.

[0047] Optionally, the number and distribution position of the pin 304 and the pin hole 204 can be set according to requirements, and the pin 304 and the pin hole 204 can be one-to-one corresponding. Specifically, the axial direction of the pin 304 and the pin hole 204 can be parallel to the Y direction, and when the number of pins 304 is greater than or equal to 2, each pin 304 can be arranged along the X direction. When the first body part 200 and the second body part 300 are installed in position, the first body part 200 and the second body part 300 are moved along the axial direction of the pin 304 to make the opposite end faces of the first body part 200 and the second body part 300 contact, at this time, the first front hook 201 and the second front hook 301 are overlapped and aligned, and the first rear hook 202 and the second rear hook 302 are overlapped and aligned.

[0048] Optionally, the pin 304 can have a circular, rectangular, polygonal or other shape in cross section, and the pin hole 204 can have a shape matching that of the pin 304 so that the pin 304 can extend into the pin hole 204 and be in clearance fit with the pin hole 204.

[0049] Referring to Figures 1 to 10 In an embodiment, the rear end hook can have an L-shaped structure as a whole, and the front end hook can also have an L-shaped structure as a whole. A limiting portion 3011 is further arranged on the front end hook, and the limiting portion 3011 cooperates with the limiting portion 3011 when the locking assembly 102 moves to the locking position to limit the front end hook from disengaging from the locking assembly 102, thereby avoiding the front end hook moving reversely out of the avoiding space 1015 and causing the first machine component 200, the second machine component 300 and the third machine component 400 to disengage.

[0050] Optionally, the first front end hook 201 and the second front end hook 301 each have a limiting portion 3011 at the end extending into the avoiding space 1015.

[0051] Referring to Figures 1 to 10 In an embodiment, the first machine component 200 and the second machine component 300 are provided with a locking mechanism for locking the first machine component 200 and the second machine component 300. The locking mechanism makes the locking between the first machine component 200 and the second machine component 300 more reliable, and the locking mechanism and the locking device 100 cooperate to realize a multiple redundancy design, thereby making the connection between the first machine component 200 and the second machine component 300 more stable and reliable.

[0052] Optionally, the locking mechanism comprises a locking seat 203 and a locking buckle 303, the locking seat 203 is arranged on one of the first body part 200 and the second body part 300, and the locking buckle 303 is arranged on the other one of the first body part 200 and the second body part 300. Further, the top of the first body part 200 and the top of the second body part 300 are concavely provided with grooves, the locking seat 203 is installed in the groove on the first body part 200, and the locking buckle 303 is installed in the groove on the second body part 300. When the first body part 200 and the second body part 300 are assembled in place, the locking buckle 303 is buckled with the locking seat 203 to achieve locking and fixing of the first body part 200 and the second body part 300. When it is needed to disassemble the first body part 200 and the second body part 300, the locking buckle 303 is flipped to make the locking buckle 303 disengage from the locking seat 203. The locking mechanism is arranged in the groove, avoiding the locking mechanism protruding from the upper surface of the first body part 200 and the second body part 300 when the aircraft is working, which is structurally neat and helps to reduce the flight resistance. The locking mechanism can adopt the locking mechanism that provides locking force by using the lever principle in the prior art, so as to eliminate the assembly gap when the first body part 200 and the second body part 300 are connected and matched. The specific structure of the existing locking mechanism will not be described here.

[0053] Optionally, the number of locking mechanisms can be set according to needs, for example, it can be one group or two groups or more. When the aircraft is small, the locking mechanism can not be needed. When the aircraft is large, the locking mechanism can be set to improve the stability and reliability of the overall structure of the aircraft and improve the safety performance.

[0054] Referring to Figures 1 to 3 , Figures 6 to 10 In an embodiment, the aircraft body quick release mechanism further comprises a first limiting structure, a second limiting structure and a third limiting structure, which are respectively used to eliminate the assembly gap of the first body part 200, the second body part 300 and the third body part 400 in the X direction, the Y direction and the Z direction, so as to reduce the vibration, abnormal sound and wear and tear of each part caused by the gap during use. When the locking device 100 locks the front hook, the X direction gap, the Y direction gap and the Z direction gap between the first body part 200, the second body part 300 and the third body part 400 are respectively eliminated by the first limiting structure, the second limiting structure and the third limiting structure.

[0055] Referring to Figures 1 to 3 , Figures 6 to 10In one embodiment, the first limiting structure includes a first limiting surface disposed on the first front end hook 201 and the second front end hook 301, a second limiting surface disposed on the locking device 100, a third limiting surface disposed on the first rear end hook 202 and the second rear end hook 302, and a fourth limiting surface disposed on the rear end hook groove 402. The first limiting surface and the second limiting surface can be tightly abutted to form a first surface contact 501, and the third limiting surface and the fourth limiting surface can be tightly abutted to form a second surface contact 502. The first surface contact 501 and the second surface contact 502 cooperate to eliminate the assembly gap of the first body component 200, the second body component 300, and the third body component 400 in the X direction. The first limiting surface, the second limiting surface, the third limiting surface, and the fourth limiting surface can be inclined surfaces. This structural design not only eliminates the gap in the X direction but also facilitates assembly guidance.

[0056] Optionally, the first limiting surface can be disposed on the side of the limiting part 3011 facing the locking block 1021, the second limiting surface can be disposed on the locking block 1021, and the fourth limiting surface is disposed on the rear hook seat 403. When the locking block 1021 moves downward to lock the front hook, the first limiting surface and the second limiting surface come into contact to form a first surface contact 501, which drives the first body component 200 and the second body component 300 to move relative to the third body component 400 in the X direction. That is, taking the third body component 400 as a reference, the first body component 200 and the second body component 300 move forward in the X direction, so that the third limiting surface and the fourth limiting surface come into closer contact to form a second surface contact 502. The cooperation of the first surface contact 501 and the second surface contact 502 can eliminate the assembly gap in the X direction.

[0057] See Figures 1 to 3 , Figures 6 to 10 In one embodiment, the second limiting structure includes a fifth limiting surface disposed on the rear hook and a sixth limiting surface disposed on the rear hook groove 402. The fifth and sixth limiting surfaces can be tightly fitted to form a third surface contact 503 and a fourth surface contact 504, thereby eliminating the assembly gap of the first body component 200, the second body component 300, and the third body component 400 along the Y-direction, that is, eliminating the assembly gap along the pin axis. The inclination of the fifth and sixth limiting surfaces are matched to ensure tight fit during assembly. The fifth limiting surface includes inclined surfaces disposed on the first rear hook 202 and the second rear hook 302, and the sixth limiting surface includes an inclined surface disposed on the groove wall of the rear hook groove 402. The groove width of the rear hook groove 402 gradually increases from the bottom to the opening. This structural design is beneficial for eliminating assembly gaps and for providing assembly guidance, thus reducing assembly difficulty.

[0058] Optionally, the first body part 200 and the second body part 300 are parts of a wing, and the wing is subjected to an upward force F most of the time during flight. For example, when the first body part 200 is fixed, the second body part 300 is subjected to the upward force F, and the first body part 200 and the second body part 300 are limited by the pin 304, so that the second body part 300 has a tendency to rotate upward along the Y direction around the center of the pin 304. In order to limit the rotation tendency of the second body part 300, the rear end hook groove 402 cooperated with the third body part 400 uses its own rigidity to limit the rotation tendency of the second body part 200, so as to achieve the locking purpose of the first body part 200 and the second body part 300. In order to eliminate a small number of unstable cases, the first body part 200 and the second body part 300 are further locked by the locking mechanism, so that the force elimination is more direct and has a redundant design, and the stability of the overall structure is further improved.

[0059] Optionally, the first body part 200 and the second body part 300 are parts of a wing, and the third body part 400 can be a vertical part. When the aircraft is in the take-off and landing stage, the third body part 400 will give the wing an upward lift F. The third body part 400 is in large area contact with the first body part 200 and the second body part 300, so that the force transmission is dispersed, and therefore it is more beneficial to large aircraft.

[0060] Referring to Figures 1 to 3 , Figures 6 to 10 In an embodiment, the third limiting structure includes a seventh limiting surface arranged on the first body part 200 and the second body part 300, an eighth limiting surface arranged on the third body part 400, a ninth limiting surface arranged on the locking device, and a tenth limiting surface arranged on the front end hook. The seventh limiting surface is in close contact with the eighth limiting surface to form a fifth surface contact 505, and the ninth limiting surface is in close contact with the tenth limiting surface to form a sixth surface contact 506. The fifth surface contact 505 and the sixth surface contact 506 cooperate to eliminate the assembly gap of the first body part 200, the second body part 300, and the third body part 400 along the Z direction.

[0061] Optionally, the seventh limiting surface includes the lower surface of the first body part 200 and the lower surface of the second body part 300, the eighth limiting surface is the upper surface of the third body part 400, and the ninth limiting surface is the lower surface of the locking piece 1021. When the locking piece 1021 moves downward to lock the front end hook, the first body part 200 and the second body part 300 are moved together with the third body part 400 along the Z direction, that is, the vertical direction. The locking piece 1021 presses the front end hook, so that the lower surface of the first body part 200, the lower surface of the second body part 300, and the upper surface of the third body part 400 are in close contact, that is, the seventh limiting surface and the eighth limiting surface are in close contact, thereby eliminating the gap along the Z direction.

[0062] The front hook slot 401, the rear hook slot 402, the front hook, the rear hook, and the locking device 100 cooperate with each other, that is, the first body part 200, the second body part 300, and the third body part 400 can be prevented from being hooked and matched, and the first body part 200, the second body part 300, and the third body part 400 can be limited and the assembly gap can be eliminated, the same part is multifunctional, has the advantages of reducing the number of parts, reducing the complexity of the mechanism, increasing stability, reducing production and installation difficulty, and the like. And the structure design makes the mechanism realize most of the embedded, adopts the embedded design, which is beneficial to reduce the protrusions on the surface of the body, thereby reducing the aerodynamic resistance during flight, and the appearance is clean, simple and beautiful.

[0063] Referring to Figure 1 , Figure 2 , Figures 6 to 8 , Figures 10 to 14 In an embodiment, the locking device 100 includes a mounting seat 101, a locking assembly 102, and a driving assembly 103. The mounting seat 101 is provided with a relief space 1015 for the front hook to move along the X direction; the locking assembly 102 is installed on the mounting seat 101; and the driving assembly 103 is connected with the locking assembly 102 and can drive the locking assembly 102 to move along the Z direction to unlock or lock the front hook.

[0064] The mounting seat 101 is provided with a relief space 1015 for the front hook to move along the X direction, so that the movement direction of the front hook during disassembly is different from the movement direction of the locking assembly 102, the requirement for the installation operation space is reduced, the operation difficulty is reduced, and the unlocking or locking is realized by driving the locking assembly to move, which is simple, convenient and fast.

[0065] Optionally, when the aircraft is in a steady state, the X direction can be a horizontal direction, the Z direction can be a vertical direction, the X direction, the Y direction, and the Z direction are perpendicular to each other, that is, the front hook can move in the relief space 1015 along the horizontal direction, and the locking assembly 102 can move up and down in the vertical direction to unlock or lock the front hook. Further, the relief space 1015 is located below the locking assembly 102, when the front hook needs to move to the relief space 1015 along the horizontal direction, the locking assembly 102 is first moved upward to the unlocked state, then the front hook moves to the relief space 1015 along the horizontal direction, and the locking assembly 102 is moved downward to the locked state, so that the front hook is pressed to remain stationary, when unlocking is needed, the locking assembly 102 is raised to release the front hook.

[0066] The structure design makes the dismounting movement direction of the front hook different from the unlocking and locking operation direction of the locking assembly 102, and is in different height planes in space height, avoids interference between the dismounting movement direction and the operation direction, improves safety performance, and reduces operation difficulty and space installation operation space requirement.

[0067] Referring to Figure 1 , Figure 2 , Figures 10 to 14 In an embodiment, the locking assembly 102 includes a locking block 1021 and a connecting rod 1022, and the driving assembly 103 is hinged to the locking block 1021 through the connecting rod 1022. The driving assembly 103 drives the connecting rod 1022 to move so as to make the locking block 1021 move along the Z direction to press or release the front hook in the avoiding space 1015. The structure is simple, and the locking block 1021 can move flexibly through the cooperation of the driving assembly 103 and the connecting rod 1022.

[0068] Optionally, the locking block 1021 and the connecting rod 1022 can be hinged through a bolt. The place where the locking block 1021 and the connecting rod 1022 are hinged is provided with an avoiding hole for providing space for the movement of the connecting rod 1022, and a strip-shaped hole is formed in the side wall of the avoiding hole. The first end of the connecting rod 1022 extends into the avoiding hole, and the bolt passes through the strip-shaped hole to connect the locking block 1021 and the connecting rod 1022 together. The strip-shaped hole and the avoiding hole are both conducive to the flexible movement of the connecting rod 1022, thereby ensuring the reliability of the movement of the locking block 1021.

[0069] Optionally, the number of the connecting rods 1022 is at least one, and the number and distribution position of the connecting rods 1022 can be set according to requirements. For example, in some large aircraft, a plurality of connecting rods 1022 can be arranged along the lifting direction of the locking block 1021, so as to make the height adjustment range wider and adapt to the requirements of different operation scenes.

[0070] Optionally, when the number of the connecting rods 1022 is greater than or equal to two, each connecting rod 1022 can be distributed along the length direction of the locking block 1021, so as to make the locking block 1021 bear force uniformly and move more stably and reliably.

[0071] Optionally, when the number of the connecting rods 1022 is two, the two connecting rods 1022 are symmetrically distributed, the first ends of the two connecting rods 1022 are hinged to the locking block 1021, the second end of one of the two connecting rods 1022 is hinged to the driving assembly 103, and the second end of the other connecting rod is hinged to the driving assembly 103 or the mounting seat 101. Further, the two connecting rods 1022 are arranged obliquely, and the oblique directions of the two connecting rods 1022 are opposite. The second ends of the two connecting rods 1022 are respectively hinged to the driving assembly 103 and the mounting seat 101, which can improve the stability and reliability of the overall structure, and is also conducive to the flexible rotation of the connecting rods 1022 around the hinge points.

[0072] Optionally, when the lock block 1021 is in the unlocking position, i.e. the lock block 1021 is raised to the highest position, the connecting rod 1022 is inclined; when the lock block 1021 is in the locking position, i.e. the lock block 1021 is lowered to the lowest position, the connecting rod 1022 is also inclined. With this structure design, it is beneficial to avoid the connecting rod 1022 from being stuck in the extreme position, and to ensure the flexibility and reliability of the movement of the connecting rod 1022.

[0073] Referring to Figure 1 , Figure 2 , Figures 10 to 14 In an embodiment, the mounting seat 101 comprises a seat body 1012, both ends of the seat body 1012 are provided with support portions 1013, the support portions 1013 are provided with guide grooves 1014 for guiding the movement of the lock block 1021 in the Z direction, the lock block 1021 is located between the two support portions 1013, and both ends of the lock block 1021 extend into the guide grooves 1014. The structure is simple, the layout is compact, the installation space is reduced, and the reliability of the lifting movement of the lock block 1021 is ensured.

[0074] Optionally, the seat body 1012 of the locking device 100 is fixedly connected with the third machine body part 400 through bolts, which is convenient to disassemble and assemble, and the connection is firm and reliable.

[0075] Optionally, the guide grooves 1014 are arranged at the top of the support portions 1013, and the avoidance space 1015 is located below the lock block 1021, i.e. the lock block 1021, the support portions 1013 and the seat body 1012 cooperatively enclose the avoidance space 1015, the space is fully utilized, the layout is compact and reasonable, and the space waste is reduced.

[0076] Referring to Figures 1 to 4 In an embodiment, the driving assembly 103 comprises a driving member 1031 and a sliding block 1032, the sliding block 1032 is slidingly installed on the mounting seat 101 and is hingedly connected with the connecting rod 1022, the driving member 1031 drives the sliding block 1032 to slide to move the connecting rod 1022, the layout is compact, the structure is simple and reliable, and the operation is convenient.

[0077] Optionally, the mounting seat 101 is provided with a limiting structure 1011, the limiting structure 1011 is used for limiting the sliding range of the sliding block 1032, so that the sliding block 1032 slides in a specified range, which is more stable and reliable.

[0078] Optionally, the limiting structure 1011 can be a limiting stopper or a limiting sliding groove. Specifically, when the limiting structure 1011 is a limiting stopper, the limiting stopper is arranged at the extreme position of the sliding block 1032 on the mounting seat 101; when the limiting structure 1011 is a limiting sliding groove, the sliding block 1032 is slidingly installed in the limiting sliding groove, and the limiting sliding groove plays a limiting and guiding role on the sliding of the sliding block 1032.

[0079] Optionally, the slider 1032 is provided with lugs on opposite sides, the limiting structure 1011 includes an end block and two side bars, one end of the two side bars is connected with the support part 1013, the other end of the two side bars is detachably connected with the end block mounted on the seat body 1012, the two side bars form a containing space for containing the slider 1032, the lugs of the slider 1032 extend into the gap between the bottom of the side bar and the seat body 1012 and can slide in the gap, the side bar limits the left and right movement of the slider 1032, and the end block and the support part 1013 connected with the side bar cooperate to limit the forward and backward movement of the slider 1032, which not only ensures smooth movement of the slider 1032 along the preset path and improves movement accuracy, but also facilitates disassembly and assembly of components.

[0080] Referring to Figures 1 to 4 In an embodiment, the driving member 1031 can be a rotating handle, the rotating handle is rotatably mounted on the mounting seat 101, the rotating handle penetrates through the slider 1032 and is threadedly connected with the slider 1032, the rotating handle rotates to drive the slider 1032 to move along the axial direction of the rotating handle, and the movement of the slider 1032 drives the connecting rod 1022 to flip to make the locking piece 1021 realize lifting. The rotating handle and the slider 1032 are threadedly connected, which can not only realize self-locking and be more safe and reliable, but also can freely control the movement speed of the slider 1032 by controlling the size of the thread pitch, save labor and energy, and the rotating handle is simple and convenient to operate, has low failure rate and can be quickly operated without the aid of tools. For example, when the thread pitch is small, the movement speed of the slider 1032 is small, but the locking force is large, which saves more labor.

[0081] Optionally, the axial direction of the rotating handle is arranged along the Y direction, that is, the axial direction of the rotating handle is parallel to the Y direction, and the rotating handle is located below the avoiding space 1015.

[0082] Optionally, the support part 1013 is provided with a mounting hole, the slider 1032 is provided with a threaded hole matched with the rotating handle in thread, one end of the rotating handle penetrates through the mounting hole and the threaded hole, and the rotating handle is limited from being separated from the mounting seat 101 by a limiting pin 1033, so that the rotating handle can only rotate along the circumferential direction thereof.

[0083] Referring to Figures 1 to 14 In an embodiment, the application further provides an aircraft, which includes the aircraft body quick release mechanism in any of the above embodiments.

[0084] The aircraft body quick release mechanism and the aircraft of the present application design the mounting or dismounting of three body parts at the same position, and only simple operation of the locking device 100 at the same position can assemble or dismount the three body parts, and the dismounting efficiency is high. In addition, the locking device 100 is designed to have a labor-saving structure and can be self-locked, and is more stable and reliable during use. The aircraft body quick release mechanism has the advantages of simple structure, low cost, light weight, convenient installation, high interchangeability, low failure rate and high reliability, and can be quickly folded and unfolded, dismounted and operated simply and quickly during the mounting and dismounting process without the need of tools, and no parts fall off during the mounting and dismounting process, which is more safe and reliable.

[0085] In the description of the present specification, the description referring to the terms "the present embodiment", "an example", "a specific example" and the like means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are contained in at least one embodiment or example of the present application. In the present specification, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0086] The above embodiments only exemplarily illustrate the principles and effects of the present application, and are not used to limit the present application. Any person skilled in the art can modify or change the above embodiments without departing from the spirit and scope of the present application. Therefore, all equivalent modifications or changes completed by those skilled in the art without departing from the spirit and technical thought disclosed by the present application should be covered by the claims of the present application.

Claims

1. An aircraft fuselage quick release mechanism, characterized in that, The aircraft body quick release mechanism comprises a first body component, a second body component, and a third body component. The first body component is provided with a first front hook. The second body component is provided with a second front hook. The third body component is provided with a front hook slot.

2. The aircraft fuselage quick disconnect mechanism of Claim 1, wherein: The front hook is movably installed in the front hook slot.

3. The aircraft fuselage quick disconnect mechanism of Claim 2, wherein: The front hook slot is provided with a locking device for locking and unlocking the front hook.

4. The aircraft fuselage quick disconnect mechanism of Claim 1, wherein: The locking device comprises a mounting seat, a locking assembly, and a driving assembly.

5. The aircraft fuselage quick disconnect mechanism of Claim 1, wherein: The mounting seat is provided with an avoiding space for the front hook to move along the X direction.

6. The aircraft fuselage quick disconnect mechanism of Claim 1, wherein: The X direction is the heading direction of the aircraft.

7. The aircraft fuselage quick disconnect mechanism of Claim 6, wherein: The driving assembly is installed on the mounting seat and connected with the locking assembly.

8. An aircraft characterized by: The driving assembly drives the locking assembly to move along the Z direction to lock or unlock the front hook. The Z direction is the vertical direction of the aircraft. When the aircraft is flying horizontally, the vertical direction is the vertical direction. The first body component is provided with a first rear hook. The second body component is provided with a second rear hook. The second rear hook is overlapped with the first rear hook to form a rear hook. The third body component is provided with a rear hook slot. The rear hook and the rear hook slot can relatively move along the X direction and be connected by hooking. The second body component is provided with a pin. The first body component is provided with a pin hole for the pin to insert and position. The first body component and the second body component are assembled along the Y direction to overlap and align the first front hook and the first rear hook with the second front hook and the second rear hook along the Y direction. The Y direction is the span direction of the aircraft. The aircraft body quick release mechanism further comprises a first limiting structure, a second limiting structure, and a third limiting structure. When the locking device locks the front hook, the X direction gap, the Y direction gap, and the Z direction gap between the first body component, the second body component, and the third body component are eliminated by the first limiting structure, the second limiting structure, and the third limiting structure respectively. The first body component and the second body component are provided with a lock mechanism. The lock mechanism is used to lock the first body component and the second body component. The driving assembly comprises a driving member and a sliding block. The sliding block is slidingly installed on the mounting seat and hinged with the connecting rod. The driving member drives the sliding block to slide to move the connecting rod. The driving member is a rotating handle. The rotating handle is rotationally installed on the mounting seat. The rotating handle penetrates through the sliding block and is threadedly connected with the sliding block. The rotating handle rotates to drive the sliding block to move along the axis of the rotating handle. The aircraft body quick release mechanism comprises any one of claims 1 to 7.

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