Undercarriage mechanism for unmanned aerial vehicle and unmanned aerial vehicle
By setting up a retraction and extension mechanism and a drive mechanism on the drone, and using a motor to drive the lead screw to rotate to realize the retraction and extension of the landing gear, the problem of load-bearing and occupation of the drone landing gear in the case of limited space is solved, and efficient space utilization and control precision are achieved.
Patent Information
- Application Number
- CN202520774875.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-22
- Publication Date
- 2026-02-27
- Estimated Expiration
- 2035-04-22
AI Technical Summary
Existing drone landing gear mechanisms are difficult to meet large load-bearing requirements in situations with limited space, and they also occupy a large amount of space, which limits the design of compact drone layouts.
The system employs a retraction and extension mechanism and a drive mechanism, including a main support arm, wheels, shock absorbers, a motor, a lead screw, a lead screw slider, and a swing arm. The motor drives the lead screw to rotate, thereby retracting and extending the landing gear. Combined with sliding rails and limiting components, it ensures that the landing gear has a large supporting force in a small space, and the lead screw motor replaces the traditional drive device.
It enables the retraction and extension of landing gear in a small space, meets the requirements of large load-bearing capacity, and is simple to control with high precision, saving cabin space and resources and reducing production costs.
Smart Images
Figure CN223949401U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to unmanned aerial vehicle structure design technical field, concretely relates to a landing gear mechanism and unmanned aerial vehicle for unmanned aerial vehicle. BACKGROUND
[0002] Generally, when designing unmanned aerial vehicle, a certain space and weight are allocated to the landing gear according to the overall layout of the aircraft. The existing unmanned aerial vehicle landing gear mechanism usually has small bearing capacity, or occupies a large space, which has certain limitations in product design. For some compact unmanned aerial vehicle models, the size of the space left for the landing gear is often very limited. For example, the landing gear position of a certain unmanned aerial vehicle is designed on the aircraft arm, which is narrow and long in shape, and the size of the landing gear in length and width direction needs to be small, and the bearing requirement of the landing gear is large. The existing landing gear mechanism cannot meet the design requirements.
[0003] In view of the above, there is an urgent need to design a landing gear mechanism and unmanned aerial vehicle for unmanned aerial vehicle which overcomes the above technical problems. INVENTION CONTENTS
[0004] The utility model aims at providing a landing gear mechanism and unmanned aerial vehicle for unmanned aerial vehicle which saves installation space, is suitable for unmanned aerial vehicle with small installation space and meets the large bearing requirement.
[0005] In order to realize the above purpose, the utility model adopts the technical scheme of a landing gear mechanism and unmanned aerial vehicle for unmanned aerial vehicle, comprising:
[0006] Two mutually symmetrical mounting plates and a folding mechanism and a driving mechanism arranged between the two mounting plates;
[0007] The folding mechanism comprises a main bearing arm rotatably connected to the mounting plate at the upper end, a wheel arranged at the lower end of the main bearing arm, and a shock absorber arranged between the side of the main bearing arm and the wheel;
[0008] The driving mechanism comprises a motor rotatably connected between the two mounting plates, a lead screw connected to the output shaft of the motor through a shaft coupling, a lead screw block threadedly connected to the outer wall of the lead screw, and a swing arm fixedly connected to the side of the main bearing arm away from the wheel, wherein the end of the swing arm away from the main bearing arm is provided with a movable slot, the lead screw block is movably arranged in the movable slot, and the two mounting plates are respectively provided with sliding rails, and the two ends of the lead screw block are respectively slidably arranged in the sliding rails.
[0009] The purpose of the utility model and the technical problems can also be further realized by the following technical measures.
[0010] Optionally, the shell of the motor is fixedly installed on a rectangular support, two sides of the rectangular support are rotatably connected with the mounting plates through second pin shafts, and second mounting pin holes for installing the second pin shafts are formed in the mounting plates.
[0011] Optionally, the swing arm is in U-shaped structure, the lower end of the swing arm is fixedly connected with the upper end of the main supporting arm, the upper ends of the two side walls of the swing arm are respectively provided with the movable grooves, and the two ends of the screw rod slider are movably arranged in the movable grooves through movable shafts.
[0012] Optionally, the two ends of the slide rail are provided with first limiting portions and second limiting portions, when the landing gear mechanism is retracted, the two ends of the movable shafts slide into the first limiting portions, and when the landing gear mechanism is lowered, the two ends of the movable shafts slide into the second limiting portions.
[0013] Optionally, a wheel fork is installed on the wheel shaft of the wheel, the two ends of the wheel fork are rotatably connected with the main supporting arm and the end of the shock absorber through third pin shafts, and the other end of the shock absorber is rotatably connected with the rear side wall of the main supporting arm through a fourth pin shaft.
[0014] Optionally, the upper ends of the main supporting arm are rotatably connected with the two mounting plates through first pin shafts, and first mounting pin holes for installing the first pin shafts are formed in the mounting plates.
[0015] The unmanned aerial vehicle comprises the landing gear mechanism for unmanned aerial vehicle.
[0016] Optionally, the unmanned aerial vehicle comprises a cabin and a cabin door, the two mounting plates are installed in the cabin through screws, and the landing gear mechanism for unmanned aerial vehicle is located in the cabin after being retracted.
[0017] Optionally, the cabin door comprises a front cabin cover and a rear cabin cover.
[0018] The front end of the front cabin cover is connected to the front side of the cabin through a torsion spring hinge, and the rear end of the rear cabin cover is fixedly connected to the side of the main supporting arm, away from the shock absorber.
[0019] The rear end of the front cabin cover abuts against the side of the rear cabin cover, away from the main supporting arm.
[0020] Optionally, the front end of the rear cabin cover is provided with an inwardly protruding and upturned portion.
[0021] Compared with the prior art, the unmanned aerial vehicle landing gear mechanism has the advantages that:
[0022] 1. The utility model discloses a landing gear mechanism for unmanned plane, which is characterized in that two installation plates connected with the unmanned plane are arranged, a retractable mechanism and a driving mechanism are arranged between the installation plates, the retractable mechanism comprises a main bearing arm, a wheel and a shock absorber, the driving mechanism is composed of a motor, a screw rod, a screw rod sliding block and a swing arm, the motor is rotatably connected between the installation plates, a sliding track is arranged on the installation plate, a movable slot is arranged on the swing arm, the two ends of the screw rod sliding block are movably arranged in the movable slot, and the two ends are slidably limited in the sliding track, the motor drives the screw rod to rotate, so that the screw rod sliding block slides on the screw rod and in the sliding track, and the screw rod sliding block can also move up and down in the movable slot, thereby driving the swing arm and the main bearing arm to rotate along the rotary connection point of the swing arm and the installation plate, so that the main bearing arm is retracted and lowered, and the landing gear is retracted and lowered. The landing gear mechanism has small size in the width and length directions, but still has large supporting force, is especially suitable for the unmanned plane with small landing gear installation space, and adopts the screw motor to replace the traditional linear rudder or stepping motor as the driving of the landing gear retraction and lowering. The screw motor control circuit is integrated on the motor, control is simple, and control precision is high.
[0023] 2. The utility model discloses a landing gear mechanism for unmanned plane, which is characterized in that a front hatch and a rear hatch are arranged on the cabin, the front end of the front hatch is connected to the front side of the cabin through a torsion spring hinge, the rear end of the rear hatch is fixedly connected to one side of the main bearing arm, the rear end of the front hatch abuts on the side of the rear hatch away from the main bearing arm, when the landing gear is lowered or retracted, the cabin door can be automatically opened or closed through the main bearing arm, and after the cabin door is closed, the whole landing gear mechanism is completely accommodated in the cabin to maintain the aerodynamic shape of the fuselage, so that the opening and closing of the cabin door does not need to increase an additional driving mechanism, which not only saves the cabin space, but also saves resources and reduces production cost. DRAWINGS
[0024] Figure 1 It is the whole structure schematic of the utility model provides landing gear mechanism for unmanned plane Figure 1 (retractable mechanism is not completely lowered)
[0025] Figure 2 It is the whole structure schematic of the utility model provides landing gear mechanism for unmanned plane Figure 2 (retractable mechanism is retracted)
[0026] Figure 3 It is the whole structure schematic of the utility model provides landing gear mechanism for unmanned plane Figure 3 (retractable mechanism is completely lowered)
[0027] Figure 4 It is the whole structure schematic of the utility model provides landing gear mechanism for unmanned plane and removes the front installation plate
[0028] Figure 5 is the front view of the mounting plate in the landing gear mechanism for unmanned aerial vehicle provided by the utility model;
[0029] Mark explanation:
[0030] 1, mounting plate; 11, sliding rail; 111, first limit part; 112, second limit part; 12, second mounting pin hole; 13, first mounting pin hole;
[0031] 2, folding mechanism; 21, main force arm; 22, wheel; 23, shock absorber; 24, fork; 25, third pin shaft; 26, fourth pin shaft; 27, first pin shaft;
[0032] 3, drive mechanism; 31, motor; 32, screw; 33, screw block; 34, swing arm; 341, movable groove; 35, L-shaped support; 36, second pin shaft; 37, movable shaft;
[0033] 4, hatch; 41, front hatch cover; 42, rear hatch cover; 43, torsion spring hinge; 44, cocking. DETAILED DESCRIPTION
[0034] In order to make the purpose, technical scheme and advantages of the utility model more clearly, the following will be further described in detail by combining with the drawings and examples. It should be understood that the specific examples described herein are only used to explain the utility model, and are not used to limit the utility model.
[0035] As shown in Figures 1 to 5 , a landing gear mechanism for unmanned aerial vehicle comprises:
[0036] Two mutually symmetrical mounting plates 1 and a folding mechanism 2 and a drive mechanism 3 arranged between the two mounting plates 1; the two mounting plates 1 are connected with the lower end of the fuselage of the unmanned aerial vehicle; the drive mechanism 3 can drive the folding mechanism 2 to be folded or unfolded;
[0037] The folding mechanism 2 comprises a main force arm 21 rotationally connected with the mounting plate 1 at the upper end, a wheel 22 arranged at the lower end of the main force arm 21 and a shock absorber 23 arranged between the side of the main force arm 21 and the wheel 22; the shock absorber 23 has a damping effect, which can be realized by using the existing technology; the main force arm 21 is driven by the drive mechanism 3 to rotate between the mounting plates 1 along the rotation connection point, so as to realize the folding of the landing gear;
[0038] The driving mechanism 3 comprises a motor 31 rotatably connected between the two mounting plates 1, a lead screw 32 connected with an output shaft of the motor 31 through a shaft coupling, a lead screw slider 33 threadedly sleeved on the outer wall of the lead screw 32, and a swing arm 34 fixedly connected with the main supporting arm 21 away from the wheel 22, wherein an active groove 341 is formed on the end of the swing arm 34 away from the main supporting arm 21, the lead screw slider 33 is movably arranged in the active groove 341, and two sliding rails 11 are respectively formed on the two mounting plates 1, and the two ends of the lead screw slider 33 are respectively slidably arranged in the sliding rails 11.
[0039] In the utility model, the motor 31 drives the lead screw 32 to rotate, so that the lead screw slider 33 slides on the lead screw 32 and in the sliding rail 11, so that the lead screw slider 33 can also move up and down in the active groove 341, so as to drive the swing arm 34 and the main supporting arm 21 to rotate along the rotary connection point with the mounting plate 1, so as to retract and lower the main supporting arm 21, and realize the retracting and lowering of the landing gear. The landing gear mechanism has small width and length, and has large supporting force, and is especially suitable for unmanned aerial vehicle with small landing gear installation space, and the lead screw motor is used to replace the traditional linear steering engine or stepping motor as the driving of the landing gear retracting and lowering, the lead screw motor control circuit is integrated on the motor, control is simple, and control precision is high.
[0040] Optionally, the shell of the motor 31 is fixedly installed on a U-shaped support 35, the two sides of the U-shaped support 35 are rotatably connected with the mounting plates 1 through second pin shafts 36, when the lead screw slider 33 slides on the lead screw 32 and the sliding rail 11, the lead screw 32 is also driven to rotate, that is, the motor 31 and the U-shaped support 35 rotate at a certain angle along the rotary connection point with the mounting plate 1, so as to realize the movement track of the lead screw slider 33, and second mounting pin holes 12 for mounting the second pin shafts 36 are formed in the mounting plates 1.
[0041] Optionally, the swing arm 34 is a U-shaped structure, which can provide installation and movement space for the lead screw 32. The lead screw 32 is located in the middle of the swing arm 34 of the U-shaped structure, and the lower end thereof is fixedly connected with the upper end of the main supporting arm 21. The upper ends of the two side walls of the swing arm 34 are respectively provided with the movement slot 341. The two ends of the lead screw sliding block 33 are movably arranged in the movement slot 341 through the movement shaft 37. The two ends of the movement shaft 37 are respectively slidably arranged in the sliding rail 11.
[0042] Optionally, the two ends of the sliding rail 11 are provided with a first limiting portion 111 and a second limiting portion 112. When the landing gear mechanism is retracted, the two ends of the movement shaft 37 slide into the first limiting portion 111. When the landing gear mechanism is lowered, the two ends of the movement shaft 37 slide into the second limiting portion 112. Figure 2 、 Figure 3 and Figure 5 When the landing gear is retracted and lowered, the first limiting portion 111 and the second limiting portion 112 can limit the lead screw sliding block 33 and the movement shaft 37 at the two ends thereof from continuing to slide. Through cooperation of the limiting position and the motor controller, the retraction and lowering state of the landing gear is controlled, so that the stability and reliability of the retraction and lowering state of the landing gear are ensured.
[0043] Optionally, the wheel shaft of the wheel 22 is provided with a wheel fork 24. The wheel fork 24 is two installation arms which are integrally connected at a certain angle. The two ends of the wheel fork 24 are respectively rotatably connected with the main supporting arm 21 and the end of the shock absorber 23 through the third pin shaft 25. The other end of the shock absorber 23 is rotatably connected with the rear side wall of the main supporting arm 21 through the fourth pin shaft 26.
[0044] Optionally, the upper ends of the main supporting arm 21 are respectively rotatably connected with the two installation plates 1 through the first pin shaft 27. The installation plate 1 is provided with the first installation pin hole 13 for installing the first pin shaft 27.
[0045] An unmanned aerial vehicle includes the unmanned aerial vehicle landing gear mechanism. The installation plate 1 is fixedly connected with the lower end of the unmanned aerial vehicle.
[0046] Optionally, the unmanned aerial vehicle includes a cabin and a cabin door 4. The two installation plates 1 are installed in the cabin through screws. The landing gear mechanism is located in the cabin after being retracted.
[0047] Optionally, the cabin door 4 includes a front cabin cover 41 and a rear cabin cover 42.
[0048] The front end of the front cabin cover 41 is connected with the front side of the cabin through a torsion spring hinge 43. The rear end of the rear cabin cover 42 is fixedly connected with the side of the main supporting arm 21 away from the shock absorber 23.
[0049] The rear end of the front hatch 41 abuts against the side of the rear hatch 42 away from the main support arm 21.
[0050] Optionally, the front end of the rear hatch 42 is provided with an inwardly protruding upturn 44. During the process of landing gear lowering, the upturn 44 of the rear hatch 42 can drive the front hatch 41 to open, and the upturn 44 will lift the front hatch 41 to a certain angle to open, as shown in FIG. Figure 3 Until the landing gear is completely lowered; when the landing gear is retracted, the torsion spring hinge 43 drives the front hatch 41 to return to the original position. The retracting mechanism and the hatch opening mechanism of the mechanism are designed integrally, and the retracting mechanism is integrated on the mounting plate, which is simple in structure and convenient for installation and maintenance.
[0051] The utility model is further described in combination with the embodiments above, but the utility model is not limited to the above-mentioned embodiments, and various changes can be made within the knowledge range possessed by those skilled in the art without departing from the purpose of the utility model.
Claims
1. An unmanned aerial vehicle landing gear mechanism, characterized in that: it comprises two mutually symmetrical mounting plates (1) and a folding mechanism (2) and a driving mechanism (3) arranged between the two mounting plates (1); the folding mechanism (2) comprises a main supporting arm (21) rotatably connected to the mounting plate (1) at the upper end, a wheel (22) arranged at the lower end of the main supporting arm (21), and a shock absorber (23) arranged between the main supporting arm (21) and the wheel (22); the driving mechanism (3) comprises a motor (31) rotatably connected between the two mounting plates (1), a lead screw (32) connected to the output shaft of the motor (31) through a shaft coupling, a lead screw slider (33) threadedly sleeved on the outer wall of the lead screw (32), and a swing arm (34) fixedly connected to the side of the main supporting arm (21) away from the wheel (22), the swing arm (34) is provided with a movable slot (341) at the end away from the main supporting arm (21), the lead screw slider (33) is movably arranged in the movable slot (341), and the two mounting plates (1) are respectively provided with sliding rails (11), and the two ends of the lead screw slider (33) are slidably arranged in the sliding rails (11). The shell of the motor (31) is fixedly installed on an I-shaped support (35), the two sides of the I-shaped support (35) are rotatably connected to the mounting plates (1) through second pin shafts (36), and the mounting plates (1) are provided with second mounting pin holes (12) for mounting the second pin shafts (36). The swing arm (34) is in U-shaped structure, the lower end of the swing arm (34) is fixedly connected to the upper end of the main supporting arm (21), the two side walls of the swing arm (34) are respectively provided with the movable slots (341) at the upper end, and the two ends of the lead screw slider (33) are movably arranged in the movable slots (341) through movable shafts (37), and the two ends of the movable shafts (37) are slidably arranged in the sliding rails (11). The two ends of the sliding rail (11) are provided with first limiting portions (111) and second limiting portions (112), when the landing gear mechanism is folded, the two ends of the movable shaft (37) slide into the first limiting portions (111), and when the landing gear mechanism is unfolded, the two ends of the movable shaft (37) slide into the second limiting portions (112).
2. The landing gear mechanism for a UAV according to claim 1, wherein, The wheel axle of the wheel (22) is provided with a yoke (24), the two ends of the yoke (24) are rotatably connected to the end portions of the main supporting arm (21) and the shock absorber (23) through third pin shafts (25), and the other end of the shock absorber (23) is rotatably connected to the rear side wall of the main supporting arm (21) through a fourth pin shaft (26).
3. The landing gear mechanism for a UAV according to claim 1, wherein, The upper ends of the main supporting arm (21) are rotatably connected to the two mounting plates (1) through first pin shafts (27), and the mounting plates (1) are provided with first mounting pin holes (13) for mounting the first pin shafts (27).
4. The landing gear mechanism for a UAV according to claim 3, wherein, 5. The landing gear mechanism for a UAV according to claim 1, wherein, 6. The landing gear mechanism for a UAV of claim 1, wherein, 7. A drone, characterized in that, The unmanned aerial vehicle landing gear mechanism comprises the unmanned aerial vehicle landing gear mechanism according to any one of claims 1-6, and the mounting plate (1) is fixedly connected to the lower end of the unmanned aerial vehicle.
8. The unmanned aerial vehicle of claim 7, wherein, The unmanned aerial vehicle comprises a cabin and a cabin door (4), and the two mounting plates (1) are installed in the cabin by screws, and the unmanned aerial vehicle landing gear mechanism is located in the cabin when being retracted.
9. The unmanned aerial vehicle of claim 8, wherein: The cabin door (4) comprises a front cabin cover (41) and a rear cabin cover (42). The front end of the front cabin cover (41) is connected to the front side of the cabin through a torsion spring hinge (43), and the rear end of the rear cabin cover (42) is fixedly connected to the side of the main force arm (21) away from the shock absorber (23). The rear end of the front cabin cover (41) abuts against the side of the rear cabin cover (42) away from the main force arm (21).
10. The unmanned aerial vehicle of claim 9, wherein, The front end of the rear cabin cover (42) is provided with an inwardly protruding and upturned portion (44).