Saucer-shaped aircraft with buffer assembly

Abstract

The invention discloses a saucer-shaped aircraft with a buffer assembly, and provides the following scheme that the saucer-shaped aircraft comprises a saucer-shaped aircraft body and the buffer assembly installed at the bottom of the saucer-shaped aircraft body, a driving structure is installed at the bottom of the saucer-shaped aircraft body, and an adjusting structure is arranged on the driving structure; by arranging a buffer assembly and an elastic structure, under the acting force of a first spring, the saucer-shaped aircraft body is protected to a certain degree, when the saucer-shaped aircraft body takes off and a buffer plate rotates to the position, close to a mounting cabinet, of a mounting frame at the end of the buffer plate, resistance of an adjusting frame to a movable plate is remarkably reduced, and at the moment, the saucer-shaped aircraft body is prevented from falling off. When the saucer-shaped aircraft takes off, the first spring releases accumulated energy and quickly pushes the movable plate to be far away from the fixed block, in the process, storage of the buffer plate is accelerated, initial lift assistance is provided for the saucer-shaped aircraft body through the elastic force effect, the saucer-shaped aircraft can quickly complete the take-off action, and energy consumption can be reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of disc-shaped aircraft, and in particular to a disc-shaped aircraft with a buffer component. Background Art

[0002] The disc-shaped aircraft is an unconventional aircraft with a wing-body fusion aerodynamic layout. Its fuselage functions as both wings and fuselage, resulting in a tailless and rudderless wing. It utilizes a hybrid control method combining variable mass moment control and thrust vectoring. This aircraft is highly integrated, with a wetted area far smaller than that of conventional aircraft of the same size. It is capable of multiple flight modes, including vertical takeoff and landing, hovering, and horizontal flight. It has broad application prospects in aerial photography, geological surveying, and emergency rescue.

[0003] The common disc-shaped aircraft on the market still have the following problems:

[0004] First, regarding the landing mechanism, existing disc-shaped aircraft typically rely on user control for landing after completing various tasks. During this process, the aircraft's legs, as key components in direct contact with the ground, have a design rationality that is directly related to the aircraft's landing safety and stability. Unfortunately, however, most disc-shaped aircraft currently on the market lack corresponding cushioning structures on their legs. When the aircraft lands, the impact force generated between the legs and the ground is directly transmitted to the aircraft itself, which not only easily causes the legs to break due to the excessive impact force, but can also trigger a series of chain reactions. For example, the strong vibrations generated during landing can quickly propagate within the aircraft, causing damage to internal parts due to uneven stress distribution, and in severe cases, even affecting the overall structure and performance of the aircraft.

[0005] In addition, existing disc-shaped aircraft also have many shortcomings in terms of take-off mechanism. Due to the lack of an effective take-off auxiliary mechanism, the aircraft must rely entirely on its own engine to generate sufficient lift to overcome ground friction and gravity during take-off. In this process, the aircraft needs to consume a large amount of energy, which not only increases the take-off cost, but also reduces the take-off efficiency. Especially under conditions with more stringent take-off conditions, such as limited take-off site, large take-off weight, etc., the existing take-off mechanism is often difficult to meet the requirements, resulting in the aircraft being unable to take off smoothly or having limited performance after take-off. In response to the above problems, this application document proposes a disc-shaped aircraft with a buffer component. Summary of the Invention

[0006] The purpose of the present invention is to address the shortcomings of the prior art and to propose a disc-shaped aircraft with a buffer component that can provide a cushioning and shock-absorbing effect during landing, and also provides an initial lift assist through elastic force, so that the take-off action can be completed quickly and energy consumption can be reduced.

[0007] In order to achieve the above object, the present invention adopts the following technical solutions:

[0008] A disc-shaped aircraft with a buffer assembly comprises a disc-shaped aircraft body and a buffer assembly mounted on the bottom of the disc-shaped aircraft body, wherein a driving structure is mounted on the bottom of the disc-shaped aircraft body, an adjustment structure is provided on the driving structure, an elastic structure is provided on the adjustment structure, and the driving structure adjusts the buffer assembly via the adjustment structure and the elastic structure, a protective structure is mounted on the buffer assembly, an inflatable structure is provided on the bottom of the disc-shaped aircraft body, and the elastic structure adjusts the inflatable structure to control the shape of the protective structure;

[0009] The buffer assembly includes a plurality of mounting blocks fixedly connected to the bottom of the saucer-shaped aircraft body, a buffer plate rotatably connected to the mounting blocks, and an adjustment frame rotatably connected to the buffer plate. The drive structure includes a mounting cabinet fixedly connected to the bottom of the saucer-shaped aircraft body, a drive motor mounted on the mounting cabinet, a drive disk fixedly connected to the output end of the drive motor, and a plurality of slide slots provided on the drive disk.

[0010] The adjusting structure includes several adjusting rods slidably connected to the installation cabinet, the top of the adjusting rod is fixedly connected to a guide block, and the guide block is slidably connected to the inside of a nearby slide groove, the elastic structure includes a fixed block fixedly connected to the adjusting rod, the fixed block is fixedly connected to a first spring on a side away from the installation block, the first spring is fixedly connected to a movable plate on a side away from the fixed block, the movable plate is rotatably connected to an end of the adjusting frame away from the buffer plate, and when the driving motor drives the driving disk to rotate, with the cooperation of the slide groove, all the adjusting rods drive all the fixed blocks to move closer to or away from each other.

[0011] Preferably, the movable plate is provided with a through hole for the adjusting rod to pass through, so that the movable plate can flexibly move on the outer wall of the adjusting rod, and the first spring is sleeved on the outer wall of the adjusting rod.

[0012] Preferably, the guide block is located inside the installation cabinet, and the fixing block is located at an end of the outer wall of the adjustment rod away from the guide block.

[0013] Preferably, one end of the buffer plate away from the mounting block is fixedly connected to a mounting bracket, and the shape of the mounting bracket is set to be a concave shape.

[0014] Preferably, the protective structure includes a connecting tube rotatably connected to the inside of the mounting frame, both sides of the connecting tube are fixedly connected to protective plates, and the outer wall of the connecting tube is fixedly connected to an airbag.

[0015] Preferably, the protective structure also includes a mounting cover fixedly connected to the outer wall of the mounting frame, a first metal pipe is connected to the mounting cover, the mounting cover and the connecting tube are connected to each other, and a plurality of vents are provided on the outer wall of the connecting tube, so that the gas can enter the interior of the connecting tube through the mounting cover, and then enter the interior of the airbag through the vents.

[0016] Preferably, the airbag is located between two protective plates, and when the airbag is inflated, the diameter is larger than the diameter of the protective plates.

[0017] Preferably, the inflatable structure includes several inflatable cylinders fixedly connected to the bottom of the disc-shaped aircraft body, an extrusion block is slidably connected inside the inflatable cylinder, a connecting rod is fixedly connected to the extrusion block, a force-bearing plate is fixedly connected to the end of the connecting rod away from the extrusion block, and a through hole is provided on the force-bearing plate for the adjustment rod to pass through.

[0018] Preferably, a second metal pipe is connected to one end of the outer wall of the inflation cylinder close to the force-bearing plate, and a rubber hose is connected to the second metal pipe, and the end of the rubber hose away from the second metal pipe is communicated with the first metal pipe, and a second spring is fixedly connected to a side of the extrusion block away from the connecting rod, and the second spring is located inside the inflation cylinder, and a support frame is fixedly connected to the outer wall of the second metal pipe, and the support frame is installed at the bottom of the saucer-shaped aircraft body.

[0019] Preferably, an anti-wear pad is fixedly connected to the outer wall of the airbag, and the shape of the anti-wear pad is set to be circular. Sealing gaskets are provided at the connection between the inflation cylinder and the connecting rod, the side of the extrusion block, and the connection between the connecting cylinder and the mounting frame.

[0020] Compared with the prior art, the present invention provides a disc-shaped aircraft with a buffer assembly, which has the following beneficial effects:

[0021] 1. The disc-shaped aircraft with a buffer assembly is provided with a buffer assembly and an elastic structure. When the disc-shaped aircraft body is landing, the driving structure is adjusted so that the adjustment structure drives all the fixed blocks to move away from each other, so that all the buffer plates automatically rotate and open. When the protective structure first contacts the ground, when the buffer plates are subjected to the impact force of the landing of the disc-shaped aircraft body, the movable plates move closer to the fixed blocks. Under the action of the first spring, the buffer plates play a buffering and shock-absorbing role, thereby playing a certain protective role for the disc-shaped aircraft body. When the disc-shaped aircraft body takes off, the driving structure rotates forward. All the fixed blocks are driven to move closer to each other through the adjustment structure. The fixed blocks squeeze the movable plate through the first spring, so that the movable plate flips the buffer plate through the adjustment frame, thereby shrinking and arranging the buffer plate. When the buffer plate rotates to the position where the mounting frame at its end is close to the mounting cabinet, the resistance of the adjustment frame to the movable plate is significantly reduced. At this time, the first spring releases the accumulated energy and quickly pushes the movable plate away from the fixed block. This process not only accelerates the storage of the buffer plate, but also provides an initial lift assist for the disc-shaped aircraft body through the elastic force, so that the disc-shaped aircraft can quickly complete the take-off action and reduce energy consumption.

[0022] 2. The disc-shaped aircraft with a buffer assembly is provided with an airbag and an inflatable structure. When the driving structure rotates forward and pushes all the fixed blocks to move away from each other, the movable plate releases the squeeze on the force-bearing plate, so that the squeeze block automatically moves away from the installation cabinet under the elastic force of the second spring, so that the gas inside the inflator can quickly pass through the second metal pipe, the rubber hose and the first metal pipe into the installation cover, and then enter the airbag through the connecting pipe and the vent hole, so that the airbag expands and forms a strong and soft buffer layer. When the disc-shaped aircraft body is in the process of landing, the anti-friction pad at the bottom of the airbag first contacts the ground , so that the airbag effectively absorbs the impact force during landing, providing preliminary cushioning protection for the aircraft; further, when the disc-shaped aircraft body completes landing and is ready to take off, or is in a parked state, the exhaust mechanism in the inflatable structure will be activated to gradually extract the gas inside the airbag. As the gas decreases, the airbag and anti-wear pad automatically and smoothly shrink into the inside of the two protective plates under the combined action of their own materials and surrounding structures. This design not only ensures that the airbag does not take up additional space when not in use, but also enables the two protective plates to act as a shielding protective layer for the airbag in the retracted state, thereby ensuring the service life and performance stability of the disc-shaped aircraft.

[0023] 3. The disc-shaped aircraft with a buffer assembly is provided with a protective structure and an anti-wear pad. When the disc-shaped aircraft body is landing, the airbag can play a buffering and shock-absorbing effect. When the disc-shaped aircraft body is preparing to take off, because the connecting tube is cleverly designed to be able to rotate freely inside the mounting frame, when the mounting frame rotates, the connecting tube and the airbag connected to it can automatically rotate accordingly, ensuring the position adjustment of the airbag during takeoff. This rotational movement of the airbag is crucial for reducing the friction between the anti-wear pad and the ground, protecting the anti-wear pad from unnecessary wear. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 A perspective view of a saucer-shaped aircraft with a buffer assembly proposed by the present invention;

[0025] Figure 2 A view of the saucer-shaped aircraft body, buffer assembly, mounting cabinet, and drive motor connection structure of the present invention;

[0026] Figure 3 A view of the connection structure of the buffer assembly, the adjustment structure, the elastic structure, the protective structure and the inflatable structure of the present invention;

[0027] Figure 4 A view of the installation cabinet, drive motor, drive disc, adjustment structure, elastic structure and buffer assembly connection structure of the present invention;

[0028] Figure 5 A view of the connection structure of the adjusting rod, the guide block, the fixed block, the first spring and the movable plate of the present invention;

[0029] Figure 6 A view of the connection structure of the fixed block, the first spring, the movable plate, the adjustment frame, the buffer plate and the mounting block of the present invention;

[0030] Figure 7 A view of the connection structure of the inflator, the extrusion block, the second spring, the connecting rod and the force-bearing plate of the present invention;

[0031] Figure 8 For the present invention Figure 6 A magnified view of the .

[0032] In the figure: 1. disc-shaped aircraft body; 2. buffer assembly; 201. mounting block; 202. buffer plate; 203. adjustment frame; 204. mounting frame; 3. driving structure; 301. mounting cabinet; 302. driving motor; 303. driving disk; 304. slide; 4. adjusting structure; 401. adjusting rod; 402. guide block; 5. elastic structure; 501. fixing block; 502. first spring; 503. movable plate; 6. protective structure; 601. connecting tube; 602. protective plate; 603. vent; 604. mounting cover; 605. first metal pipe; 606. airbag; 7. anti-wear pad; 8. inflatable structure; 801. inflatable tube; 802. extrusion block; 803. connecting rod; 804. force plate; 805. second spring; 806. second metal pipe; 807. rubber hose; 9. support frame. DETAILED DESCRIPTION

[0033] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0034] In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inside", "outside", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore should not be understood as limiting the present invention.

[0035] Example 1: Reference Figure 1-4 A disc-shaped aircraft with a buffer assembly includes a disc-shaped aircraft body 1 and a buffer assembly 2 mounted on the bottom of the disc-shaped aircraft body 1. A driving structure 3 is mounted on the bottom of the disc-shaped aircraft body 1. An adjustment structure 4 is provided on the driving structure 3. An elastic structure 5 is provided on the adjustment structure 4. The driving structure 3 adjusts the buffer assembly 2 through the adjustment structure 4 and the elastic structure 5. A protective structure 6 is mounted on the buffer assembly 2. An inflatable structure 8 is provided on the bottom of the disc-shaped aircraft body 1. The elastic structure 5 adjusts the inflatable structure 8 to control the shape of the protective structure 6.

[0036] The buffer assembly 2 includes a plurality of mounting blocks 201 fixedly connected to the bottom of the saucer-shaped aircraft body 1. A buffer plate 202 is rotatably connected to the mounting block 201, and an adjustment frame 203 is rotatably connected to the buffer plate 202. The drive structure 3 includes a mounting cabinet 301 fixedly connected to the bottom of the saucer-shaped aircraft body 1. A drive motor 302 is mounted on the mounting cabinet 301. A drive disk 303 is fixedly connected to the output end of the drive motor 302. The drive disk 303 is provided with a plurality of slide slots 304.

[0037] The adjustment structure 4 includes several adjustment rods 401 slidably connected to the installation cabinet 301, the top of the adjustment rod 401 is fixedly connected to a guide block 402, and the guide block 402 is slidably connected to the inside of the nearby slide 304, the elastic structure 5 includes a fixed block 501 fixedly connected to the adjustment rod 401, the side of the fixed block 501 away from the installation block 201 is fixedly connected to the first spring 502, the side of the first spring 502 away from the fixed block 501 is fixedly connected to a movable plate 503, the movable plate 503 is rotatably connected to the end of the adjustment frame 203 away from the buffer plate 202, when the driving motor 302 drives the driving disk 303 to rotate, with the cooperation of the slide 304, all the adjustment rods 401 drive all the fixed blocks 501 to move closer to or away from each other.

[0038] The first spring 502 is sleeved on the outer wall of the adjusting rod 401, the guide block 402 is located inside the mounting cabinet 301, and the fixed block 501 is located at the end of the outer wall of the adjusting rod 401 away from the guide block 402. By providing the through hole for the adjusting rod 401 to pass through on the movable plate 503, it is ensured that the movable plate 503 can move flexibly on the outer wall of the adjusting rod 401. That is, when the saucer-shaped aircraft body 1 is in the process of taking off, when the mounting bracket 204 at the end of the buffer plate 202 rotates to the side close to the mounting cabinet 301, under the elastic force of the first spring 502, the movable plate 503 can automatically move away from the fixed block 501 quickly, so that the buffer plate 202 can generate a certain elastic force, thereby exerting a certain upward propulsion force on the saucer-shaped aircraft body 1, so that the saucer-shaped aircraft can quickly complete the take-off action.

[0039] In the present invention, the end of the buffer plate 202 away from the mounting block 201 is fixedly connected to the mounting bracket 204, and the shape of the mounting bracket 204 is set to be a concave shape. By setting the mounting bracket 204 and setting the shape of the mounting bracket 204 to be a concave shape, it is convenient to install the connecting tube 601, the protective plate 602 and the airbag 606.

[0040] In the present invention, the protective structure 6 includes a connecting tube 601 rotatably connected to the inside of the mounting frame 204, and protective plates 602 are fixedly connected to both sides of the connecting tube 601. The outer wall of the connecting tube 601 is fixedly connected to an airbag 606. The protective structure 6 also includes a mounting cover 604 fixedly connected to the outer wall of the mounting frame 204, and a first metal pipe 605 is connected to the mounting cover 604. The mounting cover 604 is connected to the connecting tube 601. A plurality of vents 603 are provided on the outer wall of the connecting tube 601, so that the gas can enter the interior of the connecting tube 601 through the mounting cover 604, and then enter the interior of the airbag 606 through the vents 603.

[0041] In the present invention, the airbag 606 is located between the two protective plates 602, and when the airbag 606 is inflated, its diameter is larger than the diameter of the protective plate 602. By setting the protective structure 6, when the saucer-shaped aircraft body 1 is in the process of landing, the airbag 606 can play a role in buffering and shock absorption. When the saucer-shaped aircraft body 1 is ready to take off, since the connecting tube 601 is cleverly designed to be able to rotate freely inside the mounting frame 204, when the mounting frame 204 rotates, the connecting tube 601 and the airbag 606 connected thereto can automatically rotate accordingly, ensuring the position adjustment of the airbag 606 during takeoff. This rotational movement of the airbag 606 is crucial for reducing the friction between the anti-wear pad 7 and the ground, protecting the anti-wear pad 7 from unnecessary wear.

[0042] Example 2: Reference Figure 1-8On the basis of Example 1, a disc-shaped aircraft with a buffer component is provided. The inflatable structure 8 includes several inflatable cylinders 801 fixedly connected to the bottom of the disc-shaped aircraft body 1. The inflatable cylinder 801 is slidably connected to an extrusion block 802. The extrusion block 802 is fixedly connected to a connecting rod 803. The end of the connecting rod 803 away from the extrusion block 802 is fixedly connected to a force plate 804. The force plate 804 is provided with a through hole for the adjustment rod 401 to pass through. The end of the outer wall of the inflatable cylinder 801 close to the force plate 804 is connected to a second metal pipe 806, and the second metal pipe 806 is connected to a rubber hose 807. One end of the rubber hose 807 away from the second metal pipe 806 is communicated with the first metal pipe 605. The side of the extrusion block 802 away from the connecting rod 803 is fixedly connected to the second spring 805. The second spring 805 is located inside the inflatable cylinder 801. The outer wall of the second metal pipe 806 is fixedly connected to the support frame 9, and the support frame 9 is installed at the bottom of the disc-shaped aircraft body 1. By arranging the airbag 606 and the inflatable structure 8, when the driving structure 3 rotates forward and pushes all the fixed blocks 501 to move away from each other, the movable plate 503 releases the extrusion of the force-bearing plate 804, thereby allowing the extrusion block 802 to Under the elastic force of the second spring 805, it automatically moves away from the installation cabinet 301, so that the gas inside the inflatable cylinder 801 can quickly pass through the second metal pipe 806, the rubber hose 807 and the first metal pipe 605 into the installation cover 604, and then enter the airbag 606 through the connecting tube 601 and the vent 603, so that the airbag 606 expands and forms a strong and soft buffer layer. When the saucer-shaped aircraft body 1 is in the process of landing, the anti-wear pad 7 at the bottom of the airbag 606 first contacts the ground, so that the airbag 606 effectively absorbs the impact force during the landing process, providing initial support for the aircraft. Cushioning protection; further, when the saucer-shaped aircraft body 1 completes landing and is ready to take off, or is in a parked state, the exhaust mechanism in the inflatable structure 8 will be activated to gradually extract the gas inside the airbag 606. As the gas decreases, the airbag 606 and the anti-wear pad 7 automatically and smoothly shrink to the inside of the two protective plates 602 under the combined action of their own materials and surrounding structures. This design not only ensures that the airbag 606 does not take up additional space when not in use, but also enables the two protective plates 602 to act as a shielding protective layer for the airbag 606 in the contracted state, thereby ensuring the service life and performance stability of the saucer-shaped aircraft.

[0043] In the present invention, the outer wall of the airbag 606 is fixedly connected with an anti-wear pad 7, and the shape of the anti-wear pad 7 is set to be a circular ring. The connection between the inflation cylinder 801 and the connecting rod 803, the side of the extrusion block 802, and the connection between the connecting cylinder 601 and the mounting bracket 204 are all provided with sealing gaskets. By providing the anti-wear pad 7, the airbag 606 can be prevented from directly contacting the ground, thereby avoiding friction between the airbag 606 and the ground, and ensuring the service life of the airbag 606.

[0044] Working principle: When the disc-shaped aircraft body 1 is landing, the drive motor 302 rotates in the opposite direction, that is, counterclockwise. Under the action of the slide 304, the guide block 402 pushes all the fixed blocks 501 to move away from each other through the adjustment rod 401. When the fixed blocks 501 drive the movable plate 503 to move synchronously through the first spring 502, the movable plate 503 pushes the buffer plate 202 through the adjustment frame 203, so that all the buffer plates 202 automatically rotate and open;

[0045] The fixed blocks 501 move away from each other, so that the movable plate 503 releases the squeeze on the force-bearing plate 804, and thus the squeezing block 802 automatically moves away from the installation cabinet 301 under the elastic force of the second spring 805, so that the gas inside the inflatable cylinder 801 can quickly pass through the second metal pipe 806, the rubber hose 807 and the first metal pipe 605 into the installation cover 604, and then enter the airbag 606 through the connecting tube 601 and the vent 603, so that the airbag 606 expands. When the saucer-shaped aircraft body 1 is in the process of landing, the anti-wear pad 7 at the bottom of the airbag 606 first contacts the ground, thereby playing a preliminary buffering effect. When the buffer plate 202 is subjected to the impact force of the saucer-shaped aircraft body 1 when landing, the movable plate 503 moves closer to the fixed block 501. Under the action of the first spring 502, the buffer plate 202 plays a buffering and shock-absorbing effect.

[0046] When the disc-shaped aircraft body 1 is taking off, the driving motor 302 drives the driving disk 303 to rotate forward, and drives all the fixed blocks 501 to move closer to each other through the adjusting rod 401 and the guide block 402. The fixed block 501 squeezes the movable plate 503 through the first spring 502, so that the movable plate 503 flips the buffer plate 202 through the adjusting frame 203, thereby shrinking and arranging the buffer plate 202. When the buffer plate 202 rotates to the side where the mounting frame 204 at the end is close to the mounting cabinet 301, the resistance of the adjusting frame 203 to the movable plate 503 is reduced, so that the first spring 502 pushes the movable plate 503 to move quickly away from the fixed block 501, so that the buffer plate 202 can quickly bounce the disc-shaped aircraft body 1, and cooperate with the power system of the disc-shaped aircraft body 1 to complete the rapid take-off movement of the disc-shaped aircraft body 1.

[0047] After the disc-shaped aircraft body 1 takes off, as the driving motor 302 continues to rotate in the forward direction, the adjusting rod 401 squeezes the force-bearing plate 804 through the fixed block 501, the first spring 502 and the movable plate 503. The force-bearing plate 804 pushes the squeezing block 802 inside the inflatable cylinder 801 through the connecting rod 803 to move closer to the installation cabinet 301, so that the gas inside the airbag 606 is extracted, so that the airbag 606 shrinks and shrinks into the inside of the two protective plates 602.

[0048] The above are only preferred specific embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with this technical field, within the technical scope disclosed by the present invention, who makes equivalent replacements or changes based on the technical solutions and inventive concepts of the present invention, should be covered by the scope of protection of the present invention.

Claims

1. A disc-shaped aircraft with a buffer assembly, comprising a disc-shaped aircraft body (1) and a buffer assembly (2) mounted on the bottom of the disc-shaped aircraft body (1), characterized in that: A driving structure (3) is installed at the bottom of the disc-shaped aircraft body (1), an adjusting structure (4) is provided on the driving structure (3), an elastic structure (5) is provided on the adjusting structure (4), and the driving structure (3) adjusts the buffer component (2) through the adjusting structure (4) and the elastic structure (5), a protective structure (6) is installed on the buffer component (2), an inflatable structure (8) is provided at the bottom of the disc-shaped aircraft body (1), and the elastic structure (5) adjusts the inflatable structure (8), thereby controlling the shape of the protective structure (6); The buffer assembly (2) comprises a plurality of mounting blocks (201) fixedly connected to the bottom of the disc-shaped aircraft body (1), a buffer plate (202) being rotatably connected to the mounting blocks (201), an adjustment frame (203) being rotatably connected to the buffer plate (202), and the drive structure (3) comprises a mounting cabinet (301) fixedly connected to the bottom of the disc-shaped aircraft body (1), a drive motor (302) being mounted on the mounting cabinet (301), a drive disk (303) being fixedly connected to the output end of the drive motor (302), and a plurality of slide slots (304) being provided on the drive disk (303); The adjusting structure (4) includes a plurality of adjusting rods (401) slidably connected to the installation cabinet (301), the top of the adjusting rod (401) is fixedly connected with a guide block (402), and the guide block (402) is slidably connected to the inside of the adjacent slide groove (304), the elastic structure (5) includes a fixed block (501) fixedly connected to the adjusting rod (401), a side of the fixed block (501) away from the installation block (201) is fixedly connected with a first spring (502), a side of the first spring (502) away from the fixed block (501) is fixedly connected with a movable plate (503), the movable plate (503) is rotatably connected to one end of the adjusting frame (203) away from the buffer plate (202), when the driving motor (302) drives the driving disk (303) to rotate, under the cooperation of the slide groove (304), all the adjusting rods (401) drive all the fixed blocks (501) to move closer to or away from each other.

2. A disc-shaped aircraft with a buffer assembly according to claim 1, characterized in that: The movable plate (503) is provided with a through hole for the adjusting rod (401) to pass through, so that the movable plate (503) can flexibly move on the outer wall of the adjusting rod (401), and the first spring (502) is sleeved on the outer wall of the adjusting rod (401).

3. A disc-shaped aircraft with a buffer assembly according to claim 2, characterized in that: The guide block (402) is located inside the installation cabinet (301), and the fixing block (501) is located at an end of the outer wall of the adjustment rod (401) away from the guide block (402).

4. A disc-shaped aircraft with a buffer assembly according to claim 3, characterized in that: One end of the buffer plate (202) away from the mounting block (201) is fixedly connected to a mounting frame (204), and the mounting frame (204) is configured to be in a concave shape.

5. A saucer-shaped aircraft with a buffer assembly according to claim 4, characterized in that: The protective structure (6) comprises a connecting tube (601) rotatably connected to the interior of the mounting frame (204), protective plates (602) are fixedly connected to both sides of the connecting tube (601), and an air bag (606) is fixedly connected to the outer wall of the connecting tube (601).

6. A saucer-shaped aircraft with a buffer assembly according to claim 5, characterized in that: The protective structure (6) further comprises a mounting cover (604) fixedly connected to the outer wall of the mounting frame (204); a first metal pipe (605) is connected to the mounting cover (604); the mounting cover (604) and the connecting tube (601) are in communication with each other; a plurality of vent holes (603) are provided on the outer wall of the connecting tube (601), so that gas can enter the interior of the connecting tube (601) through the mounting cover (604) and then enter the interior of the airbag (606) through the vent holes (603).

7. A saucer-shaped aircraft with a buffer assembly according to claim 6, characterized in that: The airbag (606) is located between the two protective plates (602), and when the airbag (606) is inflated, its diameter is larger than the diameter of the protective plates (602).

8. A saucer-shaped aircraft with a buffer assembly according to claim 7, characterized in that: The inflatable structure (8) comprises a plurality of inflatable cylinders (801) fixedly connected to the bottom of the disc-shaped aircraft body (1); an extrusion block (802) is slidably connected inside the inflatable cylinder (801); a connecting rod (803) is fixedly connected to the extrusion block (802); a force-bearing plate (804) is fixedly connected to one end of the connecting rod (803) away from the extrusion block (802); and a through hole is provided on the force-bearing plate (804) for the adjustment rod (401) to pass through.

9. The disc-shaped aircraft with a buffer assembly according to claim 8, characterized in that: The outer wall of the inflatable cylinder (801) is connected to an end thereof close to the force-bearing plate (804), and the second metal pipe (806) is connected to a rubber hose (807). The end of the rubber hose (807) away from the second metal pipe (806) is in communication with the first metal pipe (605). The side of the extrusion block (802) away from the connecting rod (803) is fixedly connected to a second spring (805). The second spring (805) is located inside the inflatable cylinder (801). The outer wall of the second metal pipe (806) is fixedly connected to a support frame (9), and the support frame (9) is installed at the bottom of the disc-shaped aircraft body (1).

10. A saucer-shaped aircraft with a buffer assembly according to claim 9, characterized in that: The outer wall of the airbag (606) is fixedly connected with an anti-wear pad (7), and the shape of the anti-wear pad (7) is set to be annular. The connection between the inflation cylinder (801) and the connecting rod (803), the side of the extrusion block (802), and the connection between the connecting cylinder (601) and the mounting frame (204) are all provided with sealing gaskets.

Images