Buffering nose landing gear suitable for small gliding unmanned aerial vehicle
Through the three-stage spring shock absorption structure and triangular support layout, the failure of the hydraulic shock absorption system of the small gliding drone in low temperature environments is solved, and the safe take-off and efficient battery life of the drone in harsh environments is achieved, reducing maintenance difficulty and cost.
Patent Information
- Application Number
- CN202521238058.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-06-17
- Publication Date
- 2025-07-25
- Estimated Expiration
- 2035-06-17
AI Technical Summary
The hydraulic shock absorption system of the small gliding drone is prone to failure in low temperature environments, difficult maintenance, increased weight, and the single-wheel design leads to local stress concentration, affects the safety of take-off and landing and is unstable in handling on uneven grounds.
The three-stage spring shock absorbing structure and triangular bracket layout are adopted to replace the hydraulic system, and the impact force is dispersed through the multi-stage shock absorbing platform and triangular support structure, combined with wear-resistant sliding rails and elastic cushioning, achieving low-temperature stable cushioning and uniform stress.
It significantly reduces the risk of local stress concentration in landing gear, improves the safety and endurance of the take-off and landing of the drone, adapts to harsh environments, and reduces maintenance costs and weight burdens.
Smart Images
Figure CN223148735U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of unmanned aerial vehicle equipment, and in particular to a buffered front landing gear suitable for a small gliding unmanned aerial vehicle. Background Art
[0002] In the field of small gliding drones, the buffer design of the front landing gear generally follows the hydraulic shock absorption mode of traditional large aircraft. This solution relies on a hydraulic cylinder, piston and oil pipeline system, and converts the landing impact kinetic energy into heat energy through the throttling effect generated by the oil flowing through the throttle valve to achieve shock absorption. However, there are essential differences between small gliding drones and large aircraft: their take-off weight is light, their flight speed is low, and the landing impact force is much smaller than that of large aircraft, so the demand for high-load hydraulic systems is not urgent.
[0003] In the prior art, the hydraulic system of small gliding drones is composed of precision oil cylinders, seals and complex pipelines, which are prone to failure due to sand and dust pollution. Maintenance requires professional equipment cleaning, oiling and parts replacement, which is difficult to repair quickly in special environments, seriously affecting the drone's ability to continue operating. In addition, the viscosity of the hydraulic oil increases sharply and the fluidity decreases in low temperature environments, resulting in delayed or even failure of the shock absorption response. In cold areas, the landing vibration is aggravated, threatening the safety of the precision equipment on the aircraft and affecting the stability of the flight attitude. The hydraulic device needs to be equipped with control components and a large amount of oil, which significantly increases the weight of the landing gear. Small drones are extremely sensitive to weight. The additional load will shorten the cruising range by about 15%, reduce the payload capacity, and limit the flexibility of the mission. Most existing small drones use a single-wheel front landing gear design. If the attitude is slightly deviated during landing, the impact force is concentrated on a single point, which can easily cause local deformation or breakage of the landing gear; the poor adaptability to uneven roads during ground sliding aggravates the turbulence of the fuselage and affects the safety of control.
[0004] To solve the above problems, there is an urgent need for a front landing gear solution optimized for small gliding UAVs: under the premise of ensuring efficient shock absorption, it is necessary to break through the maintenance, low-temperature failure bottleneck and weight limitations of the hydraulic system, and at the same time solve the stability defects of the single-wheel design through structural innovation to improve the reliability and mission adaptability of the UAV in harsh environments. Utility Model Content
[0005] According to the technical problem raised above, a buffer front landing gear suitable for small gliding UAV is provided. The utility model adopts a three-stage spring shock-absorbing structure and a triangular bracket layout to replace the hydraulic system, realize low-temperature stable buffering, and reduce maintenance costs.
[0006] To achieve the above-mentioned purpose, the utility model provides a buffer front landing gear suitable for a small gliding UAV, comprising: a fuselage connection structure, a multi-stage shock absorbing platform, and a bottom support structure;
[0007] The fuselage connection structure includes that the secondary platform is connected to the fuselage through three lower struts and upper struts embedded with the first springs. The lower struts are connected to the second collars of the secondary platform, and the upper struts are connected to the first collars of the fuselage through the second pins and the first pins.
[0008] The multi-stage shock-absorbing platform includes a primary platform and a secondary platform, which are fixedly connected by a vertically installed second spring. The bottom end of the second spring is fixed to the primary platform, and the top end is fitted with the fixed column of the secondary platform in the vertical groove of the primary platform.
[0009] The bottom support structure includes three brackets, and each bracket is fixedly connected to the wheel through a connecting column. A metal slide rail is provided in the connecting column, and a third spring is sleeved on the slide rail. One end of the third spring is fixed to the metal plug at the outer end of the connecting column by a screw, and the other end is connected to a slider. The slider is connected to the bracket through a fourth collar, enabling the bracket to rotate freely around the fourth collar.
[0010] The bracket is sleeved on the third collar integrally formed with the primary platform. The connecting column extends upward with a vertical alloy rod, and the vertical alloy rod and the lower end of the outer metal column are fixedly connected by a fourth spring.
[0011] The three brackets and the wheels form a triangular support structure.
[0012] Further, for the second spring between the primary platform and the secondary platform, when compressed, the second spring is fitted in the vertical groove of the primary platform in a limited way, forming secondary shock absorption and displacement constraint.
[0013] Further, the surface of the metal slide rail in the connecting column is treated with wear resistance to reduce the sliding friction resistance of the slider and extend the service life of the slide rail.
[0014] Further, for the limit post connecting the secondary platform and the fuselage, the radius of the upper end of the limit post is greater than the radius of the through hole of the secondary platform.
[0015] Further, for the fourth spring between the vertical alloy rod and the outer metal column, its installation direction is perpendicular to the compression direction of the third spring in the connecting column, forming a composite shock absorption mechanism of lateral damping and longitudinal buffering.
[0016] Further, the cooperation of the third spring and the slider is used to convert the longitudinal impact force into the lateral deformation of the spring and the displacement of the slider, realizing the absorption of the first-stage shock energy.
[0017] Further, for the three brackets of the triangular support structure, the stiffness parameters of the third spring in the connecting column are designed according to the range of the landing impact force of the UAV to ensure uniform distribution of the forces on each wheel.
[0018] Further, for the fitting structure of the vertical groove of the first-level platform and the fixing column of the second-level platform, the depth of the groove matches the length of the fixing column, so that the fixing column slides along the groove in a limited way when the second spring is compressed.
[0019] Further, an elastic buffer pad is provided at the contact part between the upper end of the limiting column and the second-level platform.
[0020] Due to the adoption of the above technical solution, compared with the prior art, the utility model has the following advantages:
[0021] 1. A buffer front landing gear applicable to a small gliding unmanned aerial vehicle provided by the utility model, through the synergistic effect of a three-stage spring shock absorption structure and a triangular support layout, disperses and absorbs the landing impact force step by step, significantly reduces the risk of local stress concentration of the landing gear, and improves the takeoff and landing safety and reliability of the unmanned aerial vehicle.
[0022] 2. A buffer front landing gear applicable to a small gliding unmanned aerial vehicle provided by the utility model abandons the hydraulic device and uses a fatigue-resistant alloy spring as the core shock absorption element. The spring structure is simple, supports quick inspection and replacement, reduces the maintenance difficulty and cost. The performance of the spring is not affected by the oil viscosity, and maintains the shock absorption effect in cold / sandy environments, broadening the applicable scenarios of the unmanned aerial vehicle.
[0023] 3. A buffer front landing gear applicable to a small gliding unmanned aerial vehicle provided by the utility model forms a triangular support layout by connecting the wheels through three brackets, avoids the problem of excessive local stress of the single-wheel structure during landing, evenly disperses the impact force, and improves the structural durability of the landing gear; the triangular support cooperates with the multi-stage shock absorption system, can adapt to different landing postures and uneven ground, and ensures the takeoff and landing stability of the unmanned aerial vehicle in special environments. BRIEF DESCRIPTION OF THE DRAWINGS
[0024] In order to more clearly illustrate the technical solutions in the embodiments of the present utility model or the prior art, the following will briefly introduce the drawings required for description in the embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present utility model. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.
[0025] Figure 1 is the front view of a buffer front landing gear applicable to a small gliding unmanned aerial vehicle described in the present utility model;
[0026] Figure 2 is the side view of a buffer front landing gear applicable to a small gliding unmanned aerial vehicle described in the present utility model;
[0027] Figure 3 is the three-dimensional schematic diagram of a buffer front landing gear applicable to a small gliding unmanned aerial vehicle described in the present utility model;
[0028] Figure 4 It is a schematic structural diagram of the upper part of a buffer front landing gear applicable to a small gliding unmanned aerial vehicle according to the present utility model;
[0029] Figure 5 It is a schematic structural diagram of the upper end of a limit post of a buffer front landing gear applicable to a small gliding unmanned aerial vehicle according to the present utility model.
[0030] In the figure: 1, fuselage; 2, first collar; 3, landing gear hatch; 4, landing gear housing; 5, first pin; 6, upper strut; 7, first spring; 8, lower strut; 9, second pin; 10, second collar; 11, vertical alloy rod; 12, wheel; 13, connecting column; 14, connecting mechanism; 15, bracket; 16, outer metal column; 17, first-level platform; 18, metal plug; 19, second spring; 20, fixing column; 21, second-level platform; 22, third collar; 23, upper end of limit post; 24, limit post; 25, third spring; 26, slider; 27, fourth spring; 28, fourth collar; 29, screw. Detailed implementation manners
[0031] It should be noted that, without conflict, the embodiments in the present utility model and the features in the embodiments can be combined with each other. The present utility model will be described in detail below with reference to the drawings and in combination with the embodiments.
[0032] To make the objectives, technical solutions and advantages of the embodiments of the present utility model clearer, the technical solutions in the embodiments of the present utility model will be clearly and completely described below with reference to the drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. The description of at least one exemplary embodiment below is actually only illustrative and in no way restricts the present utility model and its application or use. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present utility model without creative efforts shall fall within the scope of protection of the present utility model.
[0033] It should be noted that the terms used here are only for describing the specific implementation manners and are not intended to limit the exemplary embodiments according to the present utility model. As used here, unless clearly specified otherwise in the context, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "include" and / or "comprise" are used in this specification, they indicate the presence of the described features, steps, operations, devices, components and / or their combinations.
[0034] Unless otherwise specifically stated, the relative arrangements, numerical expressions, and numerical values of the components and steps set forth in these embodiments do not limit the scope of the present utility model. At the same time, it should be clear that, for the sake of convenience of description, the dimensions of the various parts shown in the drawings are not drawn in actual proportional relationships. Technologies, methods, and devices known to those of ordinary skill in the relevant art may not be discussed in detail, but where appropriate, the said technologies, methods, and devices should be regarded as part of the description. In all the examples shown and discussed here, any specific values should be construed as merely exemplary and not as a limitation. Therefore, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following drawings, and thus, once an item is defined in one drawing, it does not need to be further discussed in subsequent drawings.
[0035] In the description of the present utility model, it should be understood that the orientation or positional relationships indicated by orientation words such as "front, rear, upper, lower, left, right", "lateral, vertical, perpendicular, horizontal", and "top, bottom" are generally based on the orientation or positional relationships shown in the drawings, and are only for the convenience of describing the present utility model and simplifying the description. Without contrary statements, these orientation words do not indicate and imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and thus should not be construed as limiting the protection scope of the present utility model: the orientation words "inside, outside" refer to the inside and outside relative to the contour of each component itself.
[0036] For the convenience of description, spatial relative terms such as "above...", "over...", "on the upper surface of...", "above" can be used here to describe the spatial positional relationship of a device or feature shown in the drawings with other devices or features. It should be understood that the spatial relative terms are intended to include different orientations in use or operation in addition to the orientation described in the drawings for the device. For example, if the device in the drawing is inverted, the device described as "above other devices or structures" or "over other devices or structures" will then be positioned "below other devices or structures" or "under other devices or structures". Thus, the exemplary term "above..." can include both the orientations of "above..." and "below...". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and corresponding interpretations should be made for the spatial relative descriptions used here.
[0037] In addition, it should be noted that the use of words such as "first", "second" to limit components is only for the convenience of differentiating the corresponding components. Without otherwise stating, the above words have no special meanings, and thus should not be construed as limiting the protection scope of the present utility model.
[0038] such asFigures 1 to 5 As shown, the utility model provides a buffer front landing gear suitable for a small gliding UAV, comprising: a bottom support structure, a multi-stage shock absorbing platform, and a fuselage connection structure;
[0039] The bottom support structure includes three brackets 15, each bracket 15 is connected to the connecting mechanism 14 of the wheel 12 through a connecting column 13, a metal slide rail is arranged inside the connecting column 13, a third spring 25 is sleeved on the slide rail, one end of the third spring 25 is fixed to the metal plug 18 at the outer end of the connecting column 13 by a screw 29, and the other end is connected to the slider 26, the slider 26 is connected to the bracket 15 through a fourth ring 28, so that the bracket 15 can rotate freely around the fourth ring 28, the bracket 15 is sleeved on the third ring 22 integrally formed with the first-level platform 17, the connecting column 13 extends upwardly from the vertical alloy rod 11, and the vertical alloy rod 11 is connected to the lower end of the outer metal column 16 through the fourth spring 27;
[0040] The multi-stage shock absorbing platform includes a primary platform 17 and a secondary platform 21, which are connected by a vertically installed second spring 19, the bottom end of the second spring 19 is fixed to the primary platform 17, and the top end and the fixing column 20 of the secondary platform 21 are embedded in the vertical groove of the primary platform 17;
[0041] The fuselage connection structure includes a secondary platform 21 connected to the fuselage 1 through three lower struts 8 and upper struts 6 embedded with first springs 7, and the lower struts 8 and the second ring 10 of the secondary platform 21, and the upper struts 6 and the first ring 2 of the fuselage 1 are connected through the second pin 9 and the first pin 5;
[0042] Through the bottom support structure, multi-stage shock-absorbing platform and fuselage connection structure, the impact force is absorbed step by step to reduce the vibration of the fuselage 1;
[0043] The three brackets 15 and the wheels 12 form a triangular support structure, which evenly disperses the landing impact force, avoids single-point overload, and improves landing safety.
[0044] Furthermore, the second spring 19 between the primary platform 17 and the secondary platform 21 has a bottom end fixedly connected to the primary platform 17 and a top end fixedly connected to a fixing column 20 of the secondary platform 21. When the second spring 19 is under pressure, it is limitedly engaged with the vertical groove of the primary platform 17 to form a secondary shock absorption and displacement constraint. The depth of the groove matches the length of the fixing column 20 to ensure that the fixing column 20 does not fall out of the groove when the spring is compressed.
[0045] Furthermore, the surface of the metal slide rail in the connecting column 13 is treated with wear resistance to reduce the sliding friction resistance of the slider 26 and extend the service life of the slide rail. This treatment extends the service life of the slide rail, ensures that the slider 26 slides stably on the slide rail for a long time, and avoids shock absorption failure due to wear.
[0046] Furthermore, for the limiting post 24 where the secondary platform 21 is connected to the fuselage 1, the radius of the upper end 23 of the limiting post is greater than the radius of the through hole of the secondary platform 21. When the drone takes off, the upper end 23 of the limiting post contacts the secondary platform 21, restricting the stretching amplitude of the spring and preventing the spring from being damaged due to overload.
[0047] Furthermore, for the fourth spring 27 between the vertical alloy rod 11 and the outer metal column 16, its installation direction is perpendicular to the compression direction of the third spring 25 inside the connecting column 13, forming a composite shock absorption mechanism of lateral damping and longitudinal buffering to synergistically absorb impact forces in multiple directions.
[0048] Furthermore, the cooperation between the third spring 25 and the slider 26 is used to convert the longitudinal impact force into the lateral deformation of the spring and the displacement of the slider 26. When the drone lands, the bracket 15 is pressed downward by the force, pushing the slider 26 to slide on the metal slide rail of the connecting column 13, and the third spring 25 is compressed laterally, converting the longitudinal impact force into spring deformation energy and slider 26 displacement energy to achieve primary shock absorption energy absorption.
[0049] Furthermore, for the three brackets 15 of the triangular support structure, the stiffness parameters of the third spring 25 inside the connecting column 13 are designed to match the range of the landing impact force of the drone, ensuring that the forces on each wheel 12 are evenly distributed and avoiding local stress concentration.
[0050] Furthermore, for the fitting structure of the vertical groove of the primary platform 17 and the fixing post 20 of the secondary platform 21, the depth of the groove matches the length of the fixing post 20, enabling the fixing post 20 to slide along the groove for limiting when the second spring 19 is compressed, maintaining the stability of the secondary shock absorption.
[0051] Furthermore, an elastic buffer pad is provided at the contact part between the upper end 23 of the limiting post and the secondary platform 21 to further absorb the impact force during takeoff and protect the spring and platform structure.
[0052] The overall working process of this embodiment: The landing gear door 3 opens, and the landing gear extends from the landing gear housing 4. In the primary shock absorption, at the moment when the drone lands, the wheel 12 is subjected to an impact force, the bracket 15 is pressed downward, driving the slider 26 to slide on the slide rail and compressing the third spring 25 to absorb the longitudinal impact energy, and the triangular support structure evenly distributes the impact force to the three wheels 12;
[0053] In the secondary shock absorption, the impact force is transmitted to the primary platform 17, the second spring 19 is compressed, and the fixing post 20 slides along the vertical groove for limiting to further buffer the impact force;
[0054] In the tertiary shock absorption, the remaining impact force is transmitted through the secondary platform 21 to the lower strut 8 and the upper strut 6, compressing the first spring 7, and finally transmitting the impact force to the fuselage 1 to complete the overall shock absorption.
[0055] Moreover, the upper end 23 of the limit post contacts the secondary platform 21, preventing the first spring 7 from being overstretched, protecting the spring from overload damage, and extending its service life.
[0056] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some or all of the technical features. And these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.
Claims
1. A buffer front landing gear applicable to a small gliding unmanned aerial vehicle, characterized in that, Including: Airframe connection structure, multi-stage shock-absorbing platform, bottom support structure; The airframe connection structure includes that the secondary platform is connected to the airframe through three lower struts and upper struts embedded with the first springs. The lower struts are connected to the second collar of the secondary platform, and the upper struts are connected to the first collar of the airframe through the second pin and the first pin; The multi-stage shock-absorbing platform includes a primary platform and a secondary platform, which are fixedly connected by a vertically installed second spring. The bottom end of the second spring is fixed to the primary platform, and the top end is fitted with the fixed column of the secondary platform in the vertical groove of the primary platform; The bottom support structure includes three brackets, and each bracket is fixedly connected to a wheel through a connecting column. A metal slide rail is arranged in the connecting column, and a third spring is sleeved on the slide rail; One end of the third spring is fixed to the metal plug at the outer end of the connecting column through a screw, and the other end is connected to a slider. The slider is connected to the bracket through a fourth collar, enabling the bracket to rotate freely around the fourth collar; The bracket is sleeved on the third collar integrally formed with the primary platform. The connecting column extends upward to protrude a vertical alloy rod, and the vertical alloy rod and the lower end of the outer metal column are fixedly connected by a fourth spring; The three brackets and the wheels form a triangular support structure.
2. The buffer front landing gear applicable to a small gliding unmanned aerial vehicle according to claim 1, characterized in that The second spring between the primary platform and the secondary platform is fitted and limited in the vertical groove of the primary platform when compressed, forming secondary shock absorption and displacement constraint.
3. The buffer front landing gear applicable to a small gliding unmanned aerial vehicle according to claim 2, wherein, The surface of the metal slide rail in the connecting column is treated with wear resistance to reduce the sliding friction resistance of the slider and extend the service life of the slide rail.
4. The buffer front landing gear applicable to a small gliding unmanned aerial vehicle according to claim 1, wherein The limiting column for connecting the secondary platform and the airframe, the radius of the upper end of the limiting column is larger than the radius of the through hole of the secondary platform.
5. The buffer front landing gear applicable to a small gliding unmanned aerial vehicle according to claim 1, wherein, The fourth spring between the vertical alloy rod and the outer metal column, its installation direction is perpendicular to the compression direction of the third spring in the connecting column, forming a composite shock absorption mechanism of lateral damping and longitudinal buffering.
6. The buffer front landing gear applicable to a small gliding unmanned aerial vehicle according to claim 1, wherein The cooperation of the third spring and the slider is used to convert the longitudinal impact force into the lateral deformation of the spring and the displacement of the slider, realizing the absorption of the first-stage shock energy.
7. The buffer front landing gear applicable to a small gliding unmanned aerial vehicle according to claim 1, wherein, For the three brackets of the triangular support structure, the stiffness parameters of the third spring in the connecting column are designed according to the range of the landing impact force of the UAV to ensure uniform distribution of the forces on each wheel.
8. The buffer front landing gear applicable to a small gliding unmanned aerial vehicle according to claim 1, characterized in that, For the fitting structure of the vertical groove of the primary platform and the fixed column of the secondary platform, the depth of the groove matches the length of the fixed column, enabling the fixed column to slide along the groove in a limited manner when the second spring is compressed.
9. The buffer front landing gear applicable to a small gliding unmanned aerial vehicle according to claim 4, characterized in that, An elastic buffer pad is provided at the contact part between the upper end of the limiting column and the secondary platform.