Landing supporting mechanism and aircraft
By designing a multi-stage elastic buffer landing support mechanism, the problem of the lack of independent support and buffering of existing aircraft during landing is solved, and the smooth and safe landing of the aircraft is achieved.
Patent Information
- Application Number
- CN202510408085.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-02
- Publication Date
- 2025-05-13
AI Technical Summary
The lack of independent, safe and reliable support mechanisms during landing of existing manned and unmanned aircraft has led to high requirements for pilot physical fitness and operating skills, and the rigid brackets of existing drones cannot effectively buffer the impact damage of large drones.
A landing support mechanism including a mounting base, an inner support rod, an outer support rod, a first elastic member, a second elastic member and a locking mechanism is designed. Through the expansion and retraction of the inner and outer support rods, a multi-stage elastic buffering effect is used to achieve a smooth landing of the aircraft.
Through the combined action of the first and second elastic members, two-stage buffering is achieved, which significantly reduces the impact force during landing of the aircraft and improves the stability and safety of the landing.
Smart Images
Figure CN119975767A_ABST
Abstract
Description
Technical Field
[0001] The invention belongs to the technical field of aircraft shock-absorbing support, and in particular relates to a landing support mechanism and an aircraft. Background Art
[0002] "Low-altitude economy" refers to economic activities that rely on low-altitude airspace and are dominated by the general aviation industry, involving industries and applications such as low-altitude flight, aviation tourism, scientific research and education. As an emerging industry, the low-altitude economy has a long industrial chain and strong driving force. It is widely used in the fields of medical care, meteorology, agriculture, emergency rescue, commercial flight, etc. At present, common application products can be mainly divided into manned aircraft and unmanned aircraft. Among them, manned aircraft mainly include single-person aircraft, glider aircraft, etc., and unmanned aircraft usually refers to drones. At present, manned aircraft mainly rely on the legs of the pilots as landing support when landing, and cushion by bending knees, running, etc. to achieve the purpose of safe landing; unmanned aircraft usually have a bracket at the bottom to achieve a smooth landing by controlling the speed of the propeller. However, both of the above two types of aircraft lack independent, safe and reliable support mechanisms, resulting in manned aircraft having high requirements on the physical fitness and operating skills of pilots. The brackets set by existing unmanned aircraft are usually rigid structures and lack elastic cushioning functions. For large unmanned aircraft, such as agricultural planting and rescue drones, they still face the risk of impact damage when landing. Summary of the invention
[0003] In order to solve the deficiencies of the prior art, the present invention provides a landing support mechanism and an aircraft, which can effectively improve the stability and safety of the aircraft during landing.
[0004] In order to achieve the purpose of the present invention, the following scheme is proposed: A landing support mechanism comprises: a mounting seat, an inner support rod, an outer support rod, a first elastic member, a second elastic member and a locking mechanism; The mounting base is used to connect to the aircraft; The front end of the inner support rod is rotatably mounted on the mounting seat; One end of the first elastic member is connected to the inner support rod, and the other end of the first elastic member is located below the mounting seat and connected to the mounting seat or the aircraft; The front end of the outer support rod is rotatably connected to the rear end of the inner support rod; One end of the second elastic member is arranged on the inner support rod, and the other end is arranged on the outer support rod; The locking mechanism is used to lock the outer support rod and the inner support rod after they are folded. When the outer support rod and the inner support rod are folded, the rear end of the inner support rod faces downward, the rear end of the outer support rod faces upward, and the first elastic member and the second elastic member are both in a compressed state; When the landing support mechanism is unfolded, the rear end of the inner support rod unfolds outward, and the angle between the inner support rod and the vertical plane where the front end rotation axis is located is less than or equal to 90 degrees. The rear end of the outer support rod faces downward and is lower than the bottom surface of the aircraft. The rear end of the outer support rod is located within the length range of the projection of the inner support rod on the bottom surface of the aircraft.
[0005] An aircraft comprises the above-mentioned landing support mechanism, wherein a plurality of landing support mechanisms are evenly arranged on the outside of the aircraft.
[0006] The beneficial effect of the present invention is that under the joint action of the first elastic member and the second elastic member, a two-level buffering effect is formed on the aircraft, so that the aircraft can land smoothly and the impact force of the aircraft during landing is effectively reduced, thereby ensuring the safety of the flight personnel and the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS
[0007] The drawings described herein are for illustrative purposes only of selected embodiments and not all possible implementations, and are not intended to limit the scope of the present invention.
[0008] Figure 1 The schematic diagram shows the principle of the landing support mechanism of the present application when it is folded.
[0009] Figure 2 A schematic diagram showing the principle of the landing support mechanism of the present application during deployment is shown.
[0010] Figure 3 A schematic diagram showing the principle of the landing support mechanism of the present application when it is deployed is shown.
[0011] Figure 4 A schematic diagram of a preferred structure of the first elastic member of the present application is shown.
[0012] Figure 5 A cross-sectional view of a preferred solution of the landing support mechanism of the present application when folded is shown.
[0013] Figure 6 A side view of a preferred solution of the landing support mechanism of the present application when folded is shown.
[0014] Figure 7 A view from the other side of a preferred solution of the landing support mechanism of the present application when it is folded is shown.
[0015] Figure 8 A schematic structural diagram of a preferred solution of the landing support mechanism of the present application when deployed is shown.
[0016] Fig. 9 Shows Figure 8 A partial enlarged view of point A in the middle.
[0017] Fig.10 The figure shows the installation structure diagram of the card block.
[0018] Fig.11 A cross-sectional view of a preferred solution of the landing support mechanism of the present application when deployed is shown.
[0019] Fig.12 A schematic diagram of the structure of another solution of the landing support mechanism of the present application when folded is shown.
[0020] Fig.13 A structural schematic diagram of another landing support mechanism of the application is shown when it is deployed.
[0021] Fig.14 A schematic diagram of an installation structure of a landing support mechanism on an aircraft is shown.
[0022] Fig.15 A schematic diagram showing the state of the landing support mechanism when deployed on the aircraft is shown.
[0023] Markings in the figure: mounting seat -1, connecting hole -11, inner support rod -2, through hole -21, positioning screw -22, extension plate -23, countersunk hole -231, outer support rod -3, locking tongue -31, locking hole -311, first elastic member -4, vertical section -41, inclined section -42, strip hole -421, second elastic member -5, connecting tube -51, connecting rod -52, compression spring -53, locking mechanism -6, latch -61, block -7, horizontal plate -71, vertical plate -72, rotating shaft -73, reset spring -74, buffer block -8, outer side wall -91. DETAILED DESCRIPTION
[0024] To make the objectives, technical solutions and advantages of the embodiments of the present invention more clear, the implementation modes of the present invention are described in detail below with reference to the accompanying drawings. However, the embodiments described in the present invention are only part of the embodiments of the present invention, rather than all the embodiments.
[0025] Embodiment 1, as Figures 1 to 3 As shown, a landing support mechanism includes: a mounting seat 1, an inner support rod 2, an outer support rod 3, a first elastic member 4, a second elastic member 5 and a locking mechanism 6, wherein the first elastic member 4 and the second elastic member 5 can be designed as a cylindrical spring structure.
[0026] The mounting base 1 is used to connect to the aircraft, specifically, Figures 1 to 3 and Fig.14 , Fig.15 As shown, the mounting base 1 is connected to the outer side wall 91 of the aircraft by screws or welding.
[0027] The front end of the inner support rod 2 is rotatably mounted on the mounting seat 1 .
[0028] like Figures 1 to 4 and Fig.12 , Fig.13As shown, one end of the first elastic member 4 is connected to the inner support rod 2. Preferably, the first elastic member 4 can be connected to the middle section or the front section of the inner support rod 2. The other end of the first elastic member 4 is located below the mounting seat 1 and connected to the mounting seat 1 or the aircraft.
[0029] As a preferred arrangement, the first elastic member 4 is connected to the lower end of the mounting seat 1 in this embodiment. In actual production, the mounting seat 1 can be extended downward to facilitate the connection of the first elastic member 4. This solution is not only convenient for the overall production and disassembly of the support mechanism, but also can effectively prevent the outer wall of the aircraft from generating relatively concentrated stress when the first elastic member 4 is pulled or compressed, so as to prevent the outer wall of the aircraft from deforming. On the other hand, this structure enables the first elastic member 4 and the mounting seat 1 to form an independent force system, thereby preventing the force generated between the first elastic member 4 and the aircraft from affecting the installation stability of the mounting seat 1 on the aircraft.
[0030] The front end of the outer support rod 3 is rotatably connected to the rear end of the inner support rod 2, and the axes of rotation connection at both ends of the inner support rod 2 are parallel to each other, and when the landing support mechanism is assembled to the aircraft, the axes of rotation connection at both ends of the inner support rod 2 are in a horizontal state.
[0031] One end of the second elastic member 5 is arranged on the inner support rod 2, specifically, the connection is located between the first elastic member 4 and the rear end of the inner support rod 2, and the other end of the second elastic member 5 is arranged on the outer support rod 3, specifically, the second elastic member 5 is connected to the middle section or the front section of the outer support rod 3.
[0032] The locking mechanism 6 is used to lock the outer support rod 3 and the inner support rod 2 after they are folded. Figure 1 , Figure 5 and Fig.12 As shown, when the outer support rod 3 and the inner support rod 2 are folded, the rear end of the inner support rod 2 faces downward, the rear end of the outer support rod 3 faces upward, and the first elastic member 4 and the second elastic member 5 are both in a compressed state.
[0033] like Figure 3 , Figure 8 , Fig.11 , Fig.13 As shown, when the landing support mechanism is deployed, after the locking mechanism 6 releases the outer support rod 3 and the inner support rod 2, the first elastic member 4 uses its own elastic force to push the rear end of the inner support rod 2 to deploy to the outside of the aircraft, and the angle between the inner support rod 2 and the vertical plane where the front end rotation axis is located is less than or equal to 90 degrees. The second elastic member 5 uses its own elastic force to push the rear end of the outer support rod 3 to flip outward around the front end. The rear end of the outer support rod 3 faces downward and is lower than the bottom surface of the aircraft. The rear end of the outer support rod 3 is located within the length range of the projection of the inner support rod 2 on the bottom surface of the aircraft, so that the rear end of the outer support rod 3 is inclined toward the middle of the lower part of the aircraft.
[0034] With the above solution, before the aircraft lands, the locking mechanism 6 is opened. Figure 2, Figure 3 As shown, the inner support rod 2 automatically expands outward under the elastic force of the first elastic member 4, specifically, the lower end of the inner support rod 2 swings upward toward the outside of the aircraft to achieve the purpose of expansion; the outer support rod 3 automatically expands outward under the action of the second elastic member 5, and the rear end of the outer support rod 3 swings outward. When the rear end of the outer support rod 3 is located outside the rear end of the inner support rod 2, the outer support rod 3 will quickly swing downward around the rotation axis of the rear end of the inner support rod 2 under the combined action of gravity and the second elastic member 5.
[0035] As an embodiment, when the second elastic member 5 is a cylindrical spring and its two ends are rotationally connected to the inner support rod 2 and the outer support rod 3 respectively, if the rear end of the outer support rod 3 is to be tilted toward the lower middle part of the aircraft after it is unfolded, then during the downward swinging process of the outer support rod 3, when the inner support rod 2 and the outer support rod 3 are in the same straight line, the cylindrical spring as the second elastic member 5 must be in a stretched state, so as to ensure that after the outer support rod 3 is unfolded, its rear end is tilted toward the lower middle part of the aircraft; in this way, during the downward swinging process, the outer support rod 3 will be affected by the resistance formed by the stretching of the second elastic member 5, and at this time, the gravity of the outer support rod 3 and the initial elastic force of the second elastic member 5 can be used to jointly drive the outer support rod 3 to swing downward, so as to overcome the swinging resistance generated by the second elastic member 5 on the outer support rod 3 when the second elastic member 5 is stretched.
[0036] When landing, Figure 3 As shown, the rear end of the outer support rod 3 will directly contact the ground. At the moment of contact, the aircraft will continue to descend under the action of gravity. During the continued descent of the aircraft, the angle between the inner support rod 2 and the lower end of the outer wall 91 will gradually increase, thereby stretching the first elastic member 4 to form a primary buffer to reduce the descent speed of the aircraft and reduce the downward impact of the aircraft. At the same time, the angle between the inner support rod 2 and the outer support rod 3 will be reduced, thereby compressing the second elastic member 5 to form a secondary buffer, thereby further reducing the descent speed of the aircraft and further reducing the downward impact of the aircraft. Under the joint action of the first elastic member 4 and the second elastic member 5, the aircraft lands smoothly and effectively reduces the impact force of the aircraft during landing, thereby ensuring the safety of the flight personnel and the aircraft.
[0037] Preferably, Figures 4 to 6 , Figure 8 , Fig.11As shown, the locking mechanism 6 includes a latch 61 and a lock tongue 31 vertically arranged on the outer support rod 3, a lock hole 311 is provided on the lock tongue 31, a through hole 21 is provided on the inner support rod 2, and a connecting hole 11 is provided on the bottom surface of the mounting seat 1. When the inner support rod 2 and the outer support rod 3 are folded, the lock tongue 31 passes through the through hole 21, the lock hole 311 is aligned with the connecting hole 11, and the latch 61 passes through the lock hole 311 and the connecting hole 11 at the same time, so as to lock the inner support rod 2 and the outer support rod 3. As a preferred solution, the unlocking can be performed by setting a pull rope at the bottom of the latch 61, and pulling the pull rope downward to pull the latch 61 out of the connection hole 11, and then the inner support rod 2 and the outer support rod 3 will automatically unfold under the action of the first elastic member 4 and the second elastic member 5; in order to increase the degree of automation of the unlocking process, a motor can also be set on the mounting seat 1 or the aircraft to control the extension and retraction of the latch 61, and further connect the motor to the control system of the aircraft to control the start and stop of the motor through the control system of the aircraft, and the motor can also be connected to a button controller operated by the pilot, and the pilot controls the start of the motor through the button. In addition to the above solution, a hook or a movable knot can also be used as the locking mechanism 6, both of which can realize the locking and unlocking functions of the inner support rod 2 and the outer support rod 3.
[0038] Preferably, Figure 4 , Figure 5 , Figure 8 and Fig.11 As shown, the first elastic member 4 is a spring plate structure, which includes a vertical section 41 and an inclined section 42. When the landing support mechanism is deployed, the angle between the vertical section 41 and the inclined section 42 is less than or equal to 90 degrees, so as to adapt to the condition that when the landing support mechanism is deployed, the angle between the inner support rod 2 and the vertical plane where the front end rotation axis is located is less than or equal to 90 degrees. The vertical section 41 is fixed to the mounting seat 1, and the inclined section 42 is in sliding contact with the top surface or bottom surface of the inner support rod 2. The inclined section 42 is provided with a strip hole 421 along the length direction of the inner support rod 2. The inner support rod 2 is penetrated by a positioning screw 22, and the positioning screw 22 passes through the strip hole 421. The bottom surface of the head of the positioning screw 2 is in sliding contact with the surface of the inclined section 42. The first elastic member 4 of the above structural design has a more compact installation structure, which can avoid the distortion problem of the cylindrical spring when compressed, and can ensure the normal deployment of the inner support rod 2. Moreover, the first elastic member 4 of the spring plate structure also has elastic forces in two directions, so as to meet the requirement that the first elastic member 4 is in a compressed state when the inner support rod 2 is folded, and to meet the requirement of cushioning the aircraft when the aircraft lands, and the directions of the elastic forces generated by the first elastic member 4 are opposite in the two states; during the switching process between the above two states, the inclined section 42 will move relative to the inner support rod 2 along the length direction of the inner support rod 2, so as to adapt to the change in the angle between the vertical section 41 and the inclined section 42; and the purpose of setting the positioning screw 22 is to prevent the inclined section 42 from separating from the inner support rod 2, so as to ensure that the elastic force of the first elastic member 4 can be stably and effectively transmitted to the inner support rod 2.
[0039] Preferably, Figures 4 to 9 and Figures 11 to 13 As shown, the second elastic member 5 includes a connecting tube 51 and a connecting rod 52 passing through the inside thereof. The outer ends of the connecting tube 51 and the connecting rod 52 are rotatably connected to the inner support rod 2 and the outer support rod 3 respectively. Specifically, the outer end of the connecting tube 51 can be rotatably connected to the inner support rod 2, and the outer end of the connecting rod 52 can be rotatably connected to the outer support rod 3. Alternatively, the outer end of the connecting tube 51 can be rotatably connected to the outer support rod 3, and the outer end of the connecting rod 52 can be rotatably connected to the inner support rod 2. The second elastic member 5 also includes a compression spring 53, which is passed through the interior of the connecting tube 51, or is sleeved on the outside of the connecting tube 51 and the connecting rod 52. The second elastic member 5 is subjected to pressure through the compression spring 53. During the expansion of the outer support rod 3, the connecting rod 52 is always passed through the connecting tube 51 to prevent the compression spring 53 from falling off. Compared with the cylindrical spring structure, the second elastic member 5 of the above-mentioned structural design can not only avoid the second elastic member 5 from generating swinging resistance to the outer support rod 3 during the swinging process, because both ends of the compression spring 53 do not need to be fixedly connected, it only bears pressure, and the connecting rod 52 and the connecting tube 51 can ensure the stability of the installation structure of the compression spring 53 to prevent it from falling off. Moreover, the connecting tube 51 or the connecting tube 51 and the connecting rod 52 are used to guide the compression spring 53, which can also effectively prevent the spring of the cylindrical structure of the second elastic member 5 from twisting when it is under pressure.
[0040] Preferably, Figures 5 to 11 As shown, a block 7 is provided at the rear end of the inner support rod 2. When the outer support rod 3 is unfolded, the block 7 abuts against the outer wall of the outer support rod 3 to limit the tilt state of the outer support rod 3 to prevent the outer support rod 3 from swinging upward during landing. During the unfolding of the outer support rod 3, the block 7 avoids the outer support rod 3 by swinging or extending on its own, and automatically resets and resists the outer support rod 3 after the outer support rod 3 is unfolded; the automatic swinging, extension or retraction and reset of the block 7 can be controlled by a spring or a spring sheet.
[0041] Further preferably, Fig. 9 , Fig.10As shown, the block 7 includes a horizontal plate 71 and a vertical plate 72. A rotating shaft 73 is provided at the connection between the horizontal plate 71 and the vertical plate 72. The rotating shaft 73 is parallel to the boundary line between the horizontal plate 71 and the vertical plate 72. The rear end of the inner support rod 2 is provided with extension plates 23 on both sides corresponding to the outer support rod 3. The outer support rod 3 is rotatably arranged between the two extension plates 23. A countersunk hole 231 is opened on the inner wall of the extension plate 23. The block 7 is rotatably arranged in the countersunk hole 231 through the rotating shaft 73. A reset spring 74 is provided between the vertical plate 72 and the bottom surface of the countersunk hole 231. When the reset spring 74 is in a natural state, the horizontal plate 71 is vertically toward the inner side of the extension plate 23, and the vertical plate 23 is in a state of rotation. When the outer support rod 3 is unfolded, the bottom surface of the horizontal plate 71 is used to abut the outer wall of the outer support rod 3, and the vertical plate 72 is used to abut the side wall of the outer support rod 3 to prevent the block 7 from rotating upward, thereby preventing the outer support rod 3 from swinging upward. When the outer support rod 3 swings downward, the horizontal plate 71 will be pushed to swing downward, causing the block 7 to rotate around the rotating shaft 73. At this time, the reset spring 74 will be compressed to make the horizontal plate 71 avoid the outer support rod 3. After the outer support rod 3 is unfolded, under the action of the reset spring 74, the block 7 will automatically reset, and the horizontal plate 71 and the vertical plate 72 will be used to block and limit the outer support rod 3.
[0042] Preferably, Figures 4 to 7 and Fig.12 , Fig.13 As shown, the cross section of the inner support rod 2 is a rectangular groove structure. When folded, the outer support rod 3 is buckled into the rectangular groove of the inner support rod 2, so that the structure of the support structure after folding is more compact, thereby making it more convenient to arrange and install.
[0043] Preferably, Figures 4 to 8 As shown, the cross-section of the outer support rod 3 is a rectangular groove structure. When folded, the opening direction of the rectangular groove is set relative to the opening direction of the inner support rod 2. The second elastic member 5 is arranged in the rectangular grooves of the inner support rod 2 and the outer support rod 3 to make the support structure more compact after folding, and to avoid the second elastic member 5 being blocked or interfered by the external structure when unfolded, so that the support mechanism can be unfolded safely and smoothly.
[0044] Preferably, Figures 5 to 7 As shown, a buffer block 8 is provided at the rear end of the outer support rod 3. The buffer block 8 has a honeycomb structure and absorbs impact energy through extrusion deformation. It is mainly supported by an elastic material with a large elastic modulus or a plastic material with a small rigidity. The preferred material is rubber, so as to further improve the buffering effect of the landing support mechanism on the aircraft.
[0045] Embodiment 2, an aircraft, comprising the above-mentioned landing support mechanism, such as Fig.14 , Fig.15 As shown, multiple groups of landing support mechanisms are evenly arranged on the outside of the aircraft.
[0046] Preferably, when the landing support mechanism is used for a manned aircraft, such as Fig.13 , Fig.14 As shown, one point can be set on each of the left and right sides of the aircraft corresponding to the front and back of the human body to form a four-corner support structure.
[0047] The above description is only a preferred embodiment of the present invention, and is not intended to be the only one or to limit the present invention. Those skilled in the art should understand that various changes or equivalent substitutions made to the present invention without departing from the scope of the present invention are within the scope of protection of the present invention.
Claims
1. A landing support mechanism, characterized in that: include: A mounting seat (1), an inner support rod (2), an outer support rod (3), a first elastic member (4), a second elastic member (5), and a locking mechanism (6); The mounting base (1) is used for connecting to the aircraft; The front end of the inner support rod (2) is rotatably mounted on the mounting seat (1); One end of the first elastic member (4) is connected to the inner support rod (2), and the other end of the first elastic member (4) is located below the mounting seat (1) and connected to the mounting seat (1) or the aircraft; The front end of the outer support rod (3) is rotatably connected to the rear end of the inner support rod (2); One end of the second elastic member (5) is arranged on the inner support rod (2), and the other end is arranged on the outer support rod (3); The locking mechanism (6) is used to lock the outer support rod (3) and the inner support rod (2) after they are folded. When the outer support rod (3) and the inner support rod (2) are folded, the rear end of the inner support rod (2) faces downward, the rear end of the outer support rod (3) faces upward, and the first elastic member (4) and the second elastic member (5) are both in a compressed state. When the landing support mechanism is deployed, the rear end of the inner support rod (2) is deployed outwardly, the angle between the inner support rod (2) and the vertical plane where the front rotation axis is located is less than or equal to 90 degrees, the rear end of the outer support rod (3) is downwardly facing and lower than the bottom surface of the aircraft, and the rear end of the outer support rod (3) is located within the length range of the projection of the inner support rod (2) on the bottom surface of the aircraft.
2. A landing support mechanism according to claim 1, characterized in that: The locking mechanism (6) comprises a latch (61) and a locking tongue (31) vertically arranged on the outer support rod (3); a locking hole (311) is provided on the locking tongue (31); a through hole (21) is provided on the inner support rod (2); and a connecting hole (11) is provided on the bottom surface of the mounting seat (1); when the inner support rod (2) and the outer support rod (3) are retracted, the locking tongue (31) passes through the through hole (21), the locking hole (311) is aligned with the connecting hole (11), and the latch (61) passes through the locking hole (311) and the connecting hole (11) at the same time, so as to lock the inner support rod (2) and the outer support rod (3).
3. A landing support mechanism according to claim 1, characterized in that: The first elastic member (4) is a spring plate structure, comprising a vertical section (41) and an inclined section (42). When the landing support mechanism is deployed, the angle between the vertical section (41) and the inclined section (42) is less than or equal to 90 degrees. The vertical section (41) is fixed to the mounting seat (1). The inclined section (42) is in sliding contact with the top surface or the bottom surface of the inner support rod (2). The inclined section (42) is provided with a strip hole (421) along the length direction of the inner support rod (2). The inner support rod (2) is penetrated by a positioning screw (22). The positioning screw (22) passes through the strip hole (421). The bottom surface of the head of the positioning screw (22) is in sliding contact with the surface of the inclined section (42).
4. A landing support mechanism according to claim 1, characterized in that: The second elastic member (5) comprises a connecting tube (51) and a connecting rod (52) passing through the interior of the connecting tube, and the outer ends of the connecting tube (51) and the connecting rod (52) are rotatably connected to the inner support rod (2) and the outer support rod (3) respectively; the second elastic member (5) further comprises a compression spring (53) passing through the interior of the connecting tube (51) or sleeved on the exterior of the connecting tube (51) and the connecting rod (52), and the second elastic member (5) is subjected to pressure through the compression spring (53), and the connecting rod (52) is always passed through the connecting tube (51) during the unfolding process of the outer support rod (3).
5. A landing support mechanism according to claim 1, characterized in that: A clamping block (7) is provided at the rear end of the inner support rod (2). When the outer support rod (3) is unfolded, the clamping block (7) abuts against the outer wall of the outer support rod (3) to limit the tilting state of the outer support rod (3). During the unfolding of the outer support rod (3), the clamping block (7) avoids the outer support rod (3) by swinging or extending and retracting, and automatically resets and abuts against the outer support rod (3) after the outer support rod (3) is unfolded.
6. A landing support mechanism according to claim 5, characterized in that: The block (7) comprises a horizontal plate (71) and a vertical plate (72). A rotating shaft (73) is provided at the connection between the horizontal plate (71) and the vertical plate (72). The rotating shaft (73) is parallel to the boundary line between the horizontal plate (71) and the vertical plate (72). The rear end of the inner support rod (2) is provided with extension plates (23) on both sides corresponding to the outer support rod (3). The outer support rod (3) is rotatably arranged between the two extension plates (23). The inner wall of the extension plate (23) is provided with a countersunk hole (231). The block (7) is rotated. The shaft (73) is rotatably arranged in the countersunk hole (231), and a return spring (74) is arranged between the vertical plate (72) and the bottom surface of the countersunk hole (231). When the return spring (74) is in a natural state, the horizontal plate (71) is vertically oriented toward the inside of the extension plate (23), and the vertical plate (72) is located in the countersunk hole (231). When the outer support rod (3) is unfolded, the bottom surface of the horizontal plate (71) is used to abut against the outer wall of the outer support rod (3), and the vertical plate (72) is used to abut against the side wall of the outer support rod (3).
7. A landing support mechanism according to claim 1, characterized in that: The cross section of the inner support rod (2) is a rectangular groove structure, and when folded, the outer support rod (3) is buckled into the rectangular groove of the inner support rod (2).
8. A landing support mechanism according to claim 7, characterized in that: The cross section of the outer support rod (3) is a rectangular groove structure. When folded, the opening direction of the rectangular groove is arranged opposite to the opening direction of the inner support rod (2). The second elastic member (5) is arranged in the rectangular grooves of the inner support rod (2) and the outer support rod (3).
9. A landing support mechanism according to claim 1, characterized in that: A buffer block (8) is provided at the rear end of the outer support rod (3), and the buffer block (8) is provided with a honeycomb structure.
10. An aircraft, characterized in that: The invention comprises the landing support mechanism according to any one of claims 1 to 9, wherein a plurality of landing support mechanisms are evenly arranged on the outside of the aircraft.