Landing gear and crossing machine

Abstract

The application discloses a landing gear and a crossing machine, wherein the landing gear comprises a plurality of support frames which are arranged at intervals at the bottom of the machine body and are detachably connected with the machine body; each support frame comprises a connecting member and a supporting member, the connecting member is connected with the machine body and the supporting member respectively, and the supporting member is used for supporting the machine body. The support frames arranged at the bottom are located in the lower washing airflow area of the bottom of the machine body, the exposed windward area of the landing gear is reduced by using the airflow shielding effect of the machine body, airflow separation is reduced, pressure difference resistance and vortex generation are inhibited, the structure arranged at intervals avoids excessive interference on the airflow field below the machine body, energy loss of the power system for overcoming additional resistance is effectively reduced, the single flight time of the crossing machine is prolonged, and the endurance of the crossing machine is improved.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle technology, and in particular to a landing gear and racing drone. Background Technology

[0002] Racing drones are a type of lightweight and highly maneuverable unmanned aerial vehicle (UAV) that are widely used in racing competitions, immersive aerial photography, industrial inspections, and other scenarios. Racing drones require landing gear for support and protection during flight and landing.

[0003] However, racing drones in this technology typically employ a design where landing gear is mounted on the side of the fuselage. During flight, the landing gear is directly exposed to high-speed airflow, creating a significant source of air resistance. The protruding side landing gear not only generates additional pressure drag but also creates airflow vortices at the junction of the landing gear and fuselage, further exacerbating energy loss and impacting the drone's range. Utility Model Content

[0004] The main purpose of this application is to propose a landing gear and racing drone, which aims to improve the endurance of the racing drone.

[0005] To achieve the above objectives, this application proposes a landing gear for use in a racing drone, the racing drone including a fuselage, the landing gear comprising: Multiple support frames are spaced apart at the bottom of the machine body, and the support frames are detachably connected to the machine body; The support frame includes a connecting member and a supporting member. The connecting member is connected to the body and the supporting member respectively, and the supporting member is used to support the body.

[0006] In some embodiments, the support member is rotatably connected to the connecting member.

[0007] In some embodiments, the support member includes a support body and a support arm, the support arm is connected to the support body, and one end of the support arm away from the support body is rotatably connected to the connecting member.

[0008] In some embodiments, the support arm is provided with a rotating part at one end near the connecting member, and the connecting member is provided with a matching connecting groove at one end near the rotating part. The rotating part can be embedded in the connecting groove, and the rotating part is rotatably connected to the connecting groove through a rotating shaft.

[0009] In some embodiments, the connecting member is provided with two connecting arms spaced apart on the side near the rotating part, and the connecting groove is formed between the two connecting arms. Each connecting arm is provided with a pin hole, and the rotating shaft can pass through the pin hole to connect the connecting member and the supporting member.

[0010] In some embodiments, the connecting member is provided with a claw hook on the side facing away from the connecting arm, and the claw hook is snapped into the body.

[0011] In some embodiments, three claw hooks are provided, distributed in a three-point manner on the side of the connecting member facing away from the connecting arm.

[0012] In some embodiments, the support body is provided with an anti-slip structure on the side facing away from the support arm, the anti-slip structure including a plurality of spaced grooves.

[0013] In some embodiments, any of the support frames is provided with two connecting members, and two support arms are provided accordingly, with the two support arms being rotatably connected to the two connecting members respectively.

[0014] This application also proposes a racing machine, comprising: Organism; The landing gear described above is detachably mounted to the bottom of the fuselage.

[0015] The landing gear of this application, during operation, uses connecting components to fix multiple sets of support frames at intervals to the bottom of the racing drone fuselage. Stable support is achieved by the contact between the support components and the ground, and the detachable connection allows for quick assembly and disassembly according to the needs of the flight scenario. During flight, the bottom-mounted support frames are located in the downwash airflow area at the bottom of the fuselage. Utilizing the airflow shielding effect of the fuselage, the exposed frontal area of ​​the landing gear is significantly reduced, airflow separation is reduced, and pressure drag and eddy current generation are suppressed. At the same time, the spaced structure avoids excessive interference with the airflow field below the fuselage, effectively reducing the energy loss of the power system to overcome additional drag, extending the single flight time of the racing drone, and improving the endurance of the racing drone. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the landing gear deployment structure in one embodiment of this application; Figure 2 This is a schematic diagram of the folding structure of the landing gear in one embodiment of this application; Figure 3 This is a schematic diagram illustrating the fit between the supporting member and the connecting member in one embodiment of this application; Figure 4 This is a structural schematic diagram of a connecting member in one embodiment of this application. Detailed Implementation

[0017] The solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments in this application, and not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0018] It should be noted that all directional indicators (such as up, down, left, right, front, back, etc.) in the embodiments of this application are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicator will also change accordingly.

[0019] It should also be noted that when a component is described as "fixed to" or "set on" another component, it can be directly on the other component or there may be an intervening component present. When a component is described as "connected to" another component, it can be directly connected to the other component or there may be an intervening component present.

[0020] Furthermore, the use of terms such as "first" and "second" in this application is for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. Additionally, the technical solutions of the various embodiments can be combined with each other, but only on the basis of being achievable by those skilled in the art. When the combination of technical solutions is contradictory or impossible to implement, such a combination of technical solutions should be considered non-existent and not within the scope of protection claimed in this application.

[0021] This application proposes a landing gear 100 for use in racing drones. The racing drone includes a fuselage (not shown in the figure). Please refer to [reference needed]. Figure 1 and Figure 2 In one embodiment, the landing gear 100 includes: Multiple support frames 110 are spaced apart at the bottom of the machine body, and the support frames 110 are detachably connected to the machine body; The support frame 110 includes a connecting member 111 and a supporting member 112. The connecting member 111 is connected to the machine body and the supporting member 112 respectively, and the supporting member 112 is used to support the machine body.

[0022] In this embodiment of the application, the airframe can also be referred to as the fuselage. As the core load-bearing unit, it integrates key components such as the flight control module, power system, and battery to ensure that basic flight performance is not affected.

[0023] In this application embodiment, the landing gear 100 can be configured in several ways. In a preferred embodiment, the landing gear 100 includes multiple support frames 110 spaced apart at the bottom of the fuselage. The weight of the fuselage can be borne by the multiple support frames 110, improving support stability and adapting to ground with different flatness, ensuring that the racing drone lands smoothly and avoiding damage from tipping over. In addition, compared with landing gear located on the side of the fuselage, the bottom landing gear 100 of this application is located in the downwash airflow area of ​​the fuselage during flight, and the fuselage will form a natural airflow shield for it, reducing the airflow impact intensity on the windward side of the landing gear 100. The vortex drag generated when the airflow passes through is smaller, which can effectively reduce the power consumption of the racing drone. The aerodynamic advantages of the bottom landing gear 100 can be directly converted into an increase in flight time.

[0024] In this embodiment, the number of support frames 110 can be varied. For example, there can be two or more support frames 110. In a preferred embodiment, two support frames 110 are provided. The two support frames 110 are spaced apart at the bottom of the machine body, which can keep the center of gravity of the whole machine near the central axis, avoid the center of gravity shift, and improve the stability of the machine body. Of course, the above is only an example, and the specific number can be determined according to actual needs, which is not limited in this application.

[0025] In this application embodiment, the support frame 110 can be configured in several ways. In a preferred embodiment, please refer to... Figure 1 The support frame 110 includes a connecting member 111 and a supporting member 112. The connecting member 111 is connected to the fuselage and the supporting member 112 respectively. The supporting member 112 is the part that is in direct contact with the ground, and its function is to support the fuselage on the ground or other plane. The connecting member 111 is the core of the connection between the landing gear 100 and the fuselage, and its function is to connect the landing gear 100 to the fuselage to achieve installation and fixation.

[0026] In this embodiment, the support frame 110 can be detachably connected to the body in various ways, such as snap-fit ​​connection or threaded connection, to facilitate quick assembly and use. Of course, the above are just examples, and the specific detachable connection method can be determined according to actual needs, which is not limited here.

[0027] When the operator is flying within visual range and can directly hand-launch or catch the aircraft, the landing gear 100 can be removed, which is consistent with the usage logic of the traditional gearless racing aircraft 100.

[0028] When takeoff and landing are required beyond visual range (such as long-distance aerial photography or remote area operations) or on uneven ground (such as grass, gravel, or narrow platforms), the two support frames 110 can be quickly assembled to the bottom of the fuselage via the connecting component 111.

[0029] Takeoff phase: Support component 112 provides a stable altitude for the aircraft, avoids friction between the bottom of the fuselage and the ground, ensures unobstructed propeller start-up, and a stable takeoff attitude without the need for hand-held assistance.

[0030] During landing: The two spaced support frames 110 form a stable support surface, dispersing the impact force when the fuselage lands and protecting the fuselage and internal precision components; even if there is a slight slope or bump at the landing point, the symmetrical design can reduce the risk of rollover and ensure the safe landing of the equipment.

[0031] In this embodiment of the application, the landing gear, during operation, uses connecting components 111 to fix multiple sets of support frames 110 at intervals to the bottom of the racing drone fuselage. The support components 112 contact the ground to achieve stable support, and the detachable connection allows for quick assembly and disassembly according to flight scenario requirements. During flight, the bottom-mounted support frames 110 are located in the downwash airflow area at the bottom of the fuselage. Utilizing the airflow shielding effect of the fuselage, the exposed frontal area of ​​the landing gear 100 is significantly reduced, reducing airflow separation and suppressing pressure drag and eddy current generation. At the same time, the spaced structure avoids excessive interference with the airflow field below the fuselage, effectively reducing the energy loss of the power system to overcome additional drag, extending the single flight time of the racing drone, and improving the endurance of the racing drone.

[0032] In this embodiment, the landing gear 100 also has two states: unfolded and folded, for easy storage. Specifically, the support member 112 is rotatably connected to the connecting member 111.

[0033] When the landing gear 100 is needed, the support frame 110 is first assembled to the bottom of the fuselage through the connecting component 111, and then the support component 112 is rotated from the folded state to the unfolded position, so that the two support frames 110 form a symmetrical and stable support surface.

[0034] When the landing gear 100 is not needed (e.g., for handheld flight within visual range) or needs to be stored and carried, the support component 112 can be rotated to a folded position that fits snugly against the bottom of the fuselage. At this point, the vertical volume of the entire support frame 110 is significantly reduced, fitting snugly against the bottom of the fuselage. If further weight reduction is required, the entire support frame 110 can be directly disassembled; if temporarily retained, the folded landing gear 100 does not affect handheld launch and landing operations.

[0035] In this application embodiment, the support member 112 can be configured in several ways. In a preferred embodiment, please refer to... Figure 3 The support member 112 includes a support body 1121 and a support arm 1122. The support arm 1122 is connected to the support body 1121, and the end of the support arm 1122 away from the support body 1121 is rotatably connected to the connecting member 111.

[0036] As a component that directly contacts the ground, the support body 1121 has various shape design options. In a preferred embodiment, the support body 1121 can be elongated and have arcs at both ends.

[0037] When the floor stand is needed, force can be applied to the support body 1121, thereby causing the support arm 1122 to rotate around the connecting member 111. Please refer to [reference needed]. Figure 1 When the landing gear is in the unfolded state, the support arm 1122 is generally vertically set on top of the supporting body 1121, so that the body has a certain height from the ground, avoiding friction between the body and the ground, and adapting to the take-off and landing requirements of uneven ground beyond line of sight.

[0038] When the floor stand needs to be stored, force can be applied to the support body 1121, which will cause the support arm 1122 to rotate around the connecting member 111. Please refer to [the relevant documentation / reference needed]. Figure 2 The support arm 1122 is positioned horizontally at the bottom of the aircraft, making full use of the horizontal space at the bottom of the aircraft and reducing the vertical space occupied, making it easier to store and carry the entire racing aircraft.

[0039] Please refer to Figure 3 and Figure 4 In this embodiment of the application, the support arm 1122 is provided with a rotating part 1123 at one end near the connecting member 111, and the connecting member 111 is provided with a matching connecting groove 1112 at one end near the rotating part 1123. The rotating part 1123 can be embedded in the connecting groove 1112, and the rotating part 1123 is rotatably connected to the connecting groove 1112 through a rotating shaft 1124.

[0040] In this embodiment, the rotating part 1123 can be configured in several ways. For example, the rotating part 1123 can be designed as a pin sleeve structure with a hollow channel through which the rotating shaft 1124 can pass.

[0041] In this embodiment of the application, the connecting groove 1112 may be a U-shaped groove, and the depth and width of the connecting groove 1112 are adapted to the rotating part 1123.

[0042] By fitting the rotating part 1123 into the connecting groove 1112, the groove wall can form a circumferential limit on the rotating part 1123, eliminating lateral swaying and offset during rotation, and ensuring the accurate angle of the support arm 1122 after it is unfolded.

[0043] In this application embodiment, the connecting member 111 can be configured in several ways. In a preferred embodiment, please refer to... Figure 4Two connecting arms 1111 are provided at intervals on the side of the connecting member 111 near the rotating part 1123. A connecting groove 1112 is formed between the two connecting arms 1111. Each connecting arm 1111 is provided with a pin hole 1113. The rotating shaft 1124 can pass through the pin hole 1113 to connect the connecting member 111 and the supporting member 112.

[0044] The gap between the two connecting arms 1111 is the connecting groove 1112, which can restrict the displacement of the rotating part 1123 from the left and right sides and eliminate lateral swaying. The depth of the connecting groove 1112 is matched with the diameter of the rotating part 1123, ensuring that the rotating part 1123 is completely placed in the connecting groove 1112, further improving the assembly stability.

[0045] The length of the rotating part 1123 needs to be precisely matched with the spacing between the two connecting arms 1111. After being inserted, it fits against the inner wall of the connecting arm 1111, forming a surface contact. Its hollow channel is coaxial with the pin hole 1113 of the connecting arm 1111, ensuring that the rotating shaft 1124 can simultaneously fit against the inner wall of the pin hole 1113 when it passes through, forming a three-point coaxial support structure of "rotating shaft 1124 - double pin holes 1113 - rotating part 1123". In addition, when the floor frame malfunctions, the connecting component 111 and the support component 112 can be separated by disassembling the rotating shaft 1124, making it easy to replace small parts without replacing the whole unit.

[0046] In the embodiments of this application, please refer to Figure 4 The connecting component 111 has a claw hook 1114 on the side opposite to the connecting arm 1111, and the claw hook 1114 is snapped into the machine body. The end of the claw hook 1114 is provided with a locking part, which has a certain elastic deformation capability. Its material can be a high-elasticity, high-strength engineering plastic (such as nylon, POM) or an elastic metal sheet, which can ensure that the claw hook 1114 can withstand repeated deformation without fatigue fracture, and can also provide sufficient clamping force.

[0047] By using a detachable connection method where the claw hook 1114 engages with the machine body, compared to traditional detachable methods such as threaded connections, the claw hook 1114 snap-fit ​​connection requires no tools. Assembly and disassembly of the connecting component 111 to the machine body can be completed simply by "pressing and pulling out". In addition, the connection is fully engaged and locked in place during the engagement process, eliminating the need for repeated calibration or tightening. This avoids the loosening problems that may occur with threaded connections due to insufficient tightening, thus improving the reliability and convenience of assembly.

[0048] In this application embodiment, the number of claw hooks 1114 can be set in various ways. In a preferred embodiment, please refer to [the documentation / reference needed]. Figure 4 There are three claw hooks 1114, which are distributed in a three-point manner on the side of the connecting member 111 facing away from the connecting arm 1111.

[0049] The three-point distribution forms a stable triangular support structure, which, compared to single-claw or double-claw latches, can evenly distribute the fuselage weight, flight vibration, and takeoff and landing impact forces from three directions, restricting the degrees of freedom of the connecting component 111 and preventing loosening, displacement, or swaying at the connection points. Even in extreme scenarios such as high-speed flight, sharp turns, or rough landings of the racing drone, it can ensure that the support frame 110 is firmly fixed to the fuselage, reducing the risk of accidental detachment and significantly improving flight and takeoff and landing safety.

[0050] In addition, the three-point even distribution makes the force more dispersed after engagement, with each claw hook 1114 bearing only one-third of the load, avoiding the problem of excessive local stress in double-claw or single-claw designs, reducing elastic fatigue and fracture damage caused by long-term stress concentration of the claw hook 1114, and extending the service life of the connecting component 111.

[0051] In the embodiments of this application, please refer to Figure 1 An anti-slip structure 1125 is provided on the side of the support body 1121 facing away from the support arm 1122. The anti-slip structure 1125 can be a raised texture, a dotted array of raised dots, or a removable anti-slip pad, etc. The anti-slip structure 1125 increases the ground friction of the support body 1121, counteracting the horizontal impact force during landing or the slippage caused by ground tilt, ensuring stable landing of the aircraft.

[0052] In a preferred embodiment, the anti-slip structure 1125 includes multiple spaced grooves. These grooves form an alternating concave-convex grounding structure. Upon landing, the grooves can embed into gaps or particles in soft ground, creating a physical anchoring effect and significantly enhancing the grip between the support body 1121 and the ground. Even on hard, smooth ground, the grooves can break through water films or dust layers on the grounding surface, increasing actual contact friction and effectively counteracting the tendency for the aircraft to sideslip upon landing. Furthermore, the groove structure is achieved by hollowing out redundant material. Compared to solid grounding or raised anti-slip structures 1125, this not only does not increase the weight of the support body 1121 but also moderately reduces its weight, meeting the lightweight requirements of racing drones without affecting maneuverability and endurance.

[0053] In the embodiments of this application, please refer to Figure 2 Each support frame 110 is provided with two connecting members 111, and two support arms 1122 are provided accordingly. The two support arms 1122 are rotatably connected to the two connecting members 111 respectively.

[0054] The double connecting member 111 and the double support arm 1122 form a portal frame structure, which greatly improves the torsional and bending strength and can effectively resist the impact of extreme scenarios such as tilted landing of racing aircraft and side impact, prevent the support arm 1122 from bending and the connecting member 111 from deforming, and ensure that the support frame 110 does not fail.

[0055] In addition, the dual connection structure allows the load to be evenly distributed to the two arms 1122 and the two connecting members 111 of each support frame 110, with each component bearing only a portion of the load, avoiding fatigue damage caused by stress concentration at a single point; at the same time, the three-point claw hooks 1114 of the connecting member 111 are simultaneously subjected to force, further dispersing the load-bearing pressure at the bottom of the fuselage and extending the service life of the entire landing gear 100.

[0056] This application also proposes a racing machine, comprising: Body (not shown in the picture); The landing gear 100 described above is detachable and installed on the bottom of the fuselage.

[0057] It should be noted that since the racing drone adopts all the technical solutions of all the above-mentioned landing gear 100 embodiments, the racing drone of this utility model also has at least all the beneficial effects brought about by the technical solutions of the above-mentioned embodiments, which will not be repeated here.

[0058] The above are only some or preferred embodiments of this application. Neither the text nor the drawings should limit the scope of protection of this application. All equivalent structural transformations made using the content of this application's specification and drawings under the overall concept of this application, or direct / indirect applications in other related technical fields, are included within the scope of protection of this application.

Claims

1. A landing gear for use in a racing drone, the racing drone comprising a fuselage, characterized in that, include: Multiple support frames are spaced apart at the bottom of the machine body, and the support frames are detachably connected to the machine body; The support frame includes a connecting member and a supporting member. The connecting member is connected to the body and the supporting member respectively, and the supporting member is used to support the body.

2. The landing gear according to claim 1, characterized in that, The supporting member is rotatably connected to the connecting member.

3. The landing gear according to claim 2, characterized in that, The support member includes a support body and a support arm. The support arm is connected to the support body, and the end of the support arm away from the support body is rotatably connected to the connecting member.

4. The landing gear according to claim 3, characterized in that, The support arm is provided with a rotating part at one end near the connecting member, and the connecting member is provided with a matching connecting groove at one end near the rotating part. The rotating part can be embedded in the connecting groove, and the rotating part is rotatably connected to the connecting groove through a rotating shaft.

5. The landing gear according to claim 4, characterized in that, The connecting member has two connecting arms spaced apart on the side near the rotating part, and the connecting groove is formed between the two connecting arms. Each connecting arm is provided with a pin hole, and the rotating shaft can pass through the pin hole to connect the connecting member and the supporting member.

6. The landing gear according to claim 5, characterized in that, The connecting member is provided with a claw hook on the side facing away from the connecting arm, and the claw hook is snapped into the body.

7. The landing gear according to claim 6, characterized in that, The claw hooks are provided in three positions, distributed in a three-point manner on the side of the connecting member facing away from the connecting arm.

8. The landing gear according to claim 3, characterized in that, The support body has an anti-slip structure on the side facing away from the support arm, and the anti-slip structure includes multiple spaced grooves.

9. The landing gear according to any one of claims 3 to 8, characterized in that, Each of the support frames is provided with two of the connecting members, and two support arms are provided accordingly, with the two support arms being rotatably connected to the two connecting members respectively.

10. A racing drone, characterized in that, include: Organism; The landing gear as described in any one of claims 1 to 9, wherein the landing gear is detachably mounted to the bottom of the fuselage.

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