Fuselage folding undercarriage

Abstract

The utility model belongs to the technical field of undercarriages, and particularly relates to a fuselage folding undercarriage which comprises a fixing piece and a supporting piece, the fixing piece comprises a fixing frame, the fixing frame is horizontally and fixedly installed on a fuselage, a motor is vertically fixed to the middle of the fixing frame, and a deflection strip is horizontally fixed to the output end of the motor; the two supporting pieces are symmetrically arranged at the bottom of the fixing frames, the two fixing frames are rotationally connected to the two ends of the bottom face of the fixing frames respectively, each supporting piece comprises a rotating rod, each rotating rod is rotationally connected to one end of the bottom face of the corresponding fixing frame, a supporting frame is vertically fixed to each rotating rod, and rotating column plates are horizontally arranged on the adjacent vertical end faces of the fixing frames. The folding mode of the folding supporting leg needs to rotate the supporting leg manually, the mode of rotating the supporting leg manually causes injury to personnel of the folding supporting leg by rotating paddles of the fuselage, the folding supporting leg has potential safety hazards, and the folding safety of the undercarriage in the later period is not facilitated to be improved.

Description

Technical Field

[0001] This utility model belongs to the field of landing gear technology, specifically relating to a fuselage folding landing gear. Background Technology

[0002] Unmanned aerial vehicles (UAVs), also known as unmanned aerial vehicles, have advantages such as maneuverability, rapid response, unmanned flight, and low operation requirements. Due to their good maneuverability and the ability to hover and take off and land vertically, they have low requirements for takeoff sites. Ordinary rotorcraft landing gear usually adopts a fixed structure, with the landing gear directly and vertically fixed to the UAV. The vertically exposed landing gear will increase the size of the aircraft, increase the wind resistance of the fuselage, and affect the flight stability.

[0003] An existing announcement, CN212195871U, entitled "A Landing Gear Folding and Retracting Mechanism," includes a fuselage connector, support legs, an inner spring limiting washer, a spring, an outer spring limiting washer, and a landing gear pivot. The fuselage connector is fixedly connected to one end of the landing gear pivot. A mounting hole is provided at the base of the support legs, and the inner spring limiting washer, spring, and outer spring limiting washer are all disposed within this mounting hole. The spring is positioned between the inner and outer spring limiting washers. The inner spring limiting washer is located near the fuselage connector. On one side, the other end of the landing gear pivot extends into the mounting hole. The support leg can rotate and move axially along the landing gear pivot, but cannot detach from the landing gear pivot. The fuselage connector has two limiting grooves, and the support leg has a boss at its root. The boss engages with the groove in a locked state. Pushing the support leg away from the fuselage connector and rotating it completes the switching of the boss's engagement with the two grooves. The two groove positions correspond to the landing gear retracted and deployed states. The landing gear folding and deployment mechanism is simple, reliable, and easy to manufacture, and can conveniently realize the retraction and deployment of the landing gear.

[0004] However, when the aforementioned landing gear is folded, the support feet are mainly rotated on the fuselage to change their state, thereby keeping them horizontal and reducing wind resistance. However, this method of folding the support feet requires manual rotation, which can cause injury to personnel from the rotating rotor blades. Folding the support feet poses a safety hazard and does not improve the safety of landing gear folding in the future. Utility Model Content

[0005] In view of the problems existing in the prior art, the purpose of this utility model is to provide a fuselage folding landing gear that can achieve folding without human intervention, reduce the safety hazards of folding support legs, and improve the safety of landing gear folding in the later stage.

[0006] To achieve the above objectives, this utility model provides the following technical solution:

[0007] A folding landing gear for an aircraft includes a fixing component and a support component. The fixing component includes a fixing frame, which is horizontally fixed to the fuselage. A motor is vertically fixed in the middle of the fixing frame, and a deflection bar is horizontally fixed to the output end of the motor. Two support components are symmetrically arranged at the bottom of the fixing frame, and the two fixing frames are rotatably connected to the two ends of the bottom surface of the fixing frame. The support component includes a rotating rod, which is rotatably connected to one end of the bottom surface of the fixing frame. A support frame is vertically fixed on the rotating rod. A rotating column plate is horizontally arranged on each adjacent vertical end face of the fixing frame, and the rotating column plate is rotatably hinged to the fixing frame. A pull bar is rotatably hinged to the rotating column plate, and the other end of the pull bar is rotatably connected to the end of the deflection bar.

[0008] Furthermore, both ends of the deflection bar are provided with rotating plates, and the rotating plates are rotatably connected to the ends of the deflection bar.

[0009] Furthermore, each of the top surfaces of the rotating column plate is vertically fixed with a rotating shaft, and both ends of the pull bar are vertically fixed with hinge holes, and the hinge holes at both ends of the pull bar are respectively rotatably connected to the rotating shafts of the rotating column plate of the fixed frame and the deflection bar.

[0010] Furthermore, the fixing frame has multiple vertically penetrating screw holes, and fixing bolts are installed in the multiple screw holes through the threads.

[0011] Furthermore, both ends of the fixing frame are fixed with rotating cylinders, and the end of the rotating rod is rotatably connected to the rotating cylinders.

[0012] Furthermore, a screw cylinder is vertically fixed through the bottom end face of the support frame, and a support screw is installed through the screw cylinder. A guide post is vertically fixed at the bottom end of the support screw, and a buffer is provided on the guide post.

[0013] Furthermore, the buffer includes a guide tube, which is vertically slidably inserted into the guide post, and a spring is vertically fixed at the bottom end of the guide tube. The spring is sleeved on the guide post, and the top end of the spring is fixed to the bottom end face of the support screw.

[0014] Furthermore, a base plate is fixed to the bottom end of the guide tube, and a rubber block is fixed to the bottom surface of the base plate.

[0015] Compared with the prior art, the beneficial effects of this utility model are as follows: When using the folding support component, the motor on the fixed frame is started, driving the deflection bar to deflect horizontally. The rotating column plate at the end of the deflection bar hinges and pulls the pull bar to move. As a result, the pull bar hinges and pulls the support frame on the support component to rotate at the end of the fixed frame. Thus, the deflected support frame is folded horizontally at the bottom of the fixed frame on the fuselage, thereby automatically folding the support component onto the fuselage. This keeps the support foot horizontal with the fuselage, thereby reducing the wind resistance of the support foot. The folding process does not require human intervention, reducing the safety hazards of folding the support foot and improving the safety of landing gear folding in the later stages. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0017] Figure 2 This is a schematic diagram of the overall structure of this utility model in an disassembled state;

[0018] Figure 3 This is a structural schematic diagram of the fastener of this utility model in an exploded state;

[0019] Figure 4 This is a structural schematic diagram of the support component of this utility model in an exploded state;

[0020] Figure 5 This is a schematic diagram of the structure of the buffer component of this utility model in its disassembled state.

[0021] The attached diagram lists the components represented by each number as follows:

[0022] 1. Fixing component; 11. Fixing frame; 111. Screw hole; 112. Fixing bolt; 113. Rotating drum; 12. Motor; 13. Deflection bar; 14. Tie bar; 2. Support component; 21. Rotating rod; 22. Support frame; 23. Rotating column plate; 24. Screw barrel; 25. Support screw; 26. Guide post; 27. Buffer component; 271. Guide cylinder; 272. Spring; 273. Base plate; 274. Rubber block. Detailed Implementation

[0023] To make the objectives and advantages of this utility model clearer, the following detailed description is provided in conjunction with embodiments. It should be understood that the following text is merely used to describe one or more specific embodiments of this utility model and does not strictly limit the scope of protection specifically claimed by this utility model.

[0024] like Figure 1 , Figure 2 , Figure 3 and Figure 4As shown, a fuselage folding landing gear includes a fixing component 1 and a support component 2. The fixing component 1 includes a fixing frame 11, which is horizontally fixed to the fuselage. A motor 12 is vertically fixed in the middle of the fixing frame 11, and a deflection bar 13 is horizontally fixed at the output end of the motor 12. Two support components 2 are symmetrically arranged at the bottom of the fixing frame 11, and the two fixing frames 11 are rotatably connected to the two ends of the bottom surface of the fixing frame 11 respectively. The support component 2 includes a rotating rod 21, which is rotatably connected to one end of the bottom surface of the fixing frame 11. A support frame 22 is vertically fixed on the rotating rod 21. A rotating column plate 23 is horizontally arranged on each adjacent vertical end face of the fixing frame 11, and the rotating column plate 23 is rotatably hinged to the fixing frame 11. A pull bar 14 is rotatably hinged to the rotating column plate 23, and the other end of the pull bar 14 is rotatably connected to the end of the deflection bar 13.

[0025] According to the above structure, when using the folding support 2, the motor 12 on the fixed frame 11 is started to drive the deflection bar 13 to deflect horizontally. The rotating column plate 23 at the end of the deflection bar 13 is hinged to pull the pull bar 14 to move. As a result, the pull bar 14 hinged to pull the support frame 22 on the support 2 to rotate at the end of the fixed frame 11. As a result, the deflected support frame 22 is folded horizontally at the bottom of the fixed frame 11 of the fuselage, thereby automatically folding the support 2 onto the fuselage. This keeps the support foot horizontal with the fuselage, thereby reducing the wind resistance of the support foot. The folding process does not require human intervention, reducing the safety hazards of folding the support foot and improving the safety of the landing gear folding in the later stage.

[0026] like Figure 3 As shown, both ends of the deflection bar 13 are provided with rotating column plates 23, and the rotating column plates 23 are rotatably connected to the ends of the deflection bar 13.

[0027] According to the above structure, the rotating plate 23 hinged at both ends of the deflection bar 13 is used to change the position of the deflection bar 14 when it is pulled during the later deflection, so as to prevent the bar 14 from getting stuck and unable to move.

[0028] like Figure 2 , Figure 3 and Figure 4 As shown, a rotating shaft is vertically fixed on the top surface of the rotating column plate 23, and hinge holes are vertically fixed at both ends of the pull bar 14. The hinge holes at both ends of the pull bar 14 are rotatably connected to the rotating shaft of the rotating column plate 23 of the fixed frame 11 and the deflection bar 13, respectively.

[0029] According to the above structure, the rotating shaft provided on the rotating column plate 23 is used to rotate the hinged pull bar 14. At the same time, the hinge hole at the end of the pull bar 14 is hinged to the rotating shaft of the rotating column plate 23, so as to facilitate the later pulling of the support member 2 to rotate and fold on the fixed frame 11.

[0030] like Figure 3As shown, the fixing bracket 11 has multiple vertically through screw holes 111, and the screw holes 111 are threaded together to install fixing bolts 112.

[0031] According to the above structure, a fixing bolt 112 is threaded through the screw hole 111 on the fixing bracket 11 and is fixedly installed on the machine body by means of the fixing bolt 112.

[0032] like Figure 3 As shown, both ends of the fixed frame 11 are fixed with rotating cylinders 113, and the end of the rotating rod 21 is rotatably connected to the rotating cylinders 113.

[0033] According to the above structure, the rotating cylinder 113 at the end of the fixed frame 11 is rotatably connected to the rotating rod 21 and is used to rotate and unfold the support member 2 to fold and extend the landing gear.

[0034] like Figure 4 As shown, a screw cylinder 24 is vertically fixed through the bottom surface of the support frame 22, and a support screw 25 is installed through the screw cylinder 24. A guide post 26 is vertically fixed at the bottom end of the support screw 25, and a buffer 27 is provided on the guide post 26.

[0035] Based on the above structure, during use, depending on the terrain of the take-off and landing location, the support screw 25 in the screw cylinder 24 of the support frame 22 is rotated in advance, and the threaded pushes the buffer 27 to move, adjusting the distance between the buffer 27 and the support frame 22 to adapt to different terrain take-off and landing requirements.

[0036] like Figure 5 As shown, the buffer 27 includes a guide tube 271, which is vertically slidably inserted into the guide post 26. A spring 272 is vertically fixed at the bottom end of the guide tube 271. The spring 272 is sleeved on the guide post 26, and the top end of the spring 272 is fixed on the bottom end face of the support screw 25.

[0037] According to the above structure, the inertial weight of the fuselage during takeoff and landing causes the guide cylinder 271 on the buffer 27 to slide vertically on the guide post 26, compressing the deformation of the spring 272 to reduce the inertial force, resulting in instability of the fuselage.

[0038] like Figure 5 As shown, a base plate 273 is fixed to the bottom end of the guide tube 271, and a rubber block 274 is fixed to the bottom surface of the base plate 273.

[0039] According to the above structure, the rubber block 274 on the bottom plate 273 of the guide cylinder 271 increases the friction with the bottom surface and reduces slippage. At the same time, the deformation of the rubber block 274 absorbs the inertial pressure during take-off and landing.

[0040] The working principle of this utility model is as follows: When using the folding support 2, the motor 12 on the fixed frame 11 is started, which drives the deflection bar 13 to deflect horizontally. The rotating column plate 23 at the end of the deflection bar 13 is hinged to pull the pull bar 14 to move. As a result, the pull bar 14 hinged to pull the support frame 22 on the support 2 to rotate at the end of the fixed frame 11. As a result, the deflected support frame 22 is folded horizontally at the bottom of the fixed frame 11 of the machine body, thereby automatically folding the support 2 onto the machine body.

[0041] The above description is merely a preferred embodiment of this utility model. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principle of this utility model, and these improvements and modifications should also be considered within the scope of protection of this utility model. Structures, devices, and operating methods not specifically described or explained in this utility model, unless otherwise specified or limited, shall be implemented using conventional methods in the field.

Claims

1. A folding landing gear for a fuselage, characterized in that The utility model provides a kind of fixed frame (11) and support (2) including fixed frame (11), the fixed frame (11) is horizontally fixedly installed on machine body, and the middle part of fixed frame (11) is vertically fixed with motor (12), the output end of motor (12) is horizontally fixed with deflection strip (13), the support (2) is symmetrically provided with two in the bottom of fixed frame (11), and two fixed frame (11) is respectively rotationally connected in the bottom surface both ends of fixed frame (11), the support (2) includes rotary rod (21), the rotary rod (21) is rotationally connected in the bottom surface one end of fixed frame (11), and rotary rod (21) is vertically fixed with support frame (22), the adjacent vertical end surface of fixed frame (11) is horizontally provided with rotary column plate (23), and rotary column plate (23) is rotationally hinged on fixed frame (11) on rotary column plate (23), rotary column plate (23) is rotationally hinged with pull strip (14), and the other end of pull strip (14) is rotationally connected in the end of deflection strip (13).

2. A folding landing gear for a fuselage according to claim 1, characterized in that: The both ends of the deflection strip (13) are provided with the rotary column plate (23), and the rotary column plate (23) is rotationally connected with the end of the deflection strip (13).

3. A folding landing gear for a fuselage according to claim 2, characterised in that: The top surface of the rotary column plate (23) is vertically fixed with a rotating shaft, and the both ends of the pull strip (14) are vertically fixed with a hinge hole, and the hinge holes at the both ends of the pull strip (14) are rotationally connected with the rotating shafts of the rotary column plates (23) of the fixed frame (11) and the deflection strip (13) respectively.

4. A folding landing gear for a fuselage according to claim 1, characterized in that: A plurality of screw holes (111) are vertically and through provided in the fixed frame (11), and the plurality of screw holes (111) are threadedly and through installed with fixed bolts (112).

5. A folding landing gear for a fuselage according to claim 4, characterised in that: Both ends of the fixed frame (11) are fixed with rotary cylinders (113), and the end of the rotary rod (21) is rotationally connected with the rotary cylinder (113).

6. A folding landing gear for a fuselage according to claim 1, characterized in that: A screw cylinder (24) is vertically and through fixed in the bottom end surface of the support frame (22), and a support screw rod (25) is threadedly and through installed in the screw cylinder (24), and a guide column (26) is vertically fixed in the bottom end of the support screw rod (25), and a buffer (27) is provided in the guide column (26).

7. A folding landing gear for a fuselage according to claim 6, characterised in that: The buffer (27) includes a guide cylinder (271), the guide cylinder (271) is vertically and slidingly inserted in the guide column (26), and a spring (272) is vertically fixed in the bottom end of the guide cylinder (271), the spring (272) is sleeved on the guide column (26), and the top end of the spring (272) is fixed on the bottom end surface of the support screw rod (25).

8. A folding landing gear for a fuselage according to claim 7, characterised in that: The bottom end of the guide cylinder (271) is fixed with a bottom plate (273), and a rubber block (274) is fixed on the bottom surface of the bottom plate (273).

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