An unmanned aerial vehicle crash landing device incorporating an airbag

Abstract

The application discloses a kind of unmanned plane forced landing device combined air bag, including: main unit, including unmanned plane main body and fixedly connected in the outside symmetry distribution of unmanned plane main body fixed block;The application utilizes blocking board, so that load-bearing base and holding plate can be placed in the bottom of unmanned plane main body Medical equipment, in turn, the maneuverability of unmanned plane is used to quickly transport medical equipment to the designated area, in turn, to a certain extent, through the air bag inside landing buffer unit, protection treatment is carried out during unmanned plane landing process, using first buffer air bag, so that equipment can pass through multiple groups of air bags distributed in different areas of equipment, so that the impact force received by equipment can be reduced to a certain extent when unmanned plane landing and ground contact, and at the same time, the parachute built-in fixed pipe is ejected, further improve the equipment's buffer landing effect through parachute, so as to improve the equipment's buffer forced landing effect to a certain extent.

Description

Technical Field

[0001] This invention relates to the field of drone emergency landing device technology, and in particular to a drone emergency landing device incorporating an airbag. Background Technology

[0002] Due to its flexibility and efficiency, drone technology is increasingly being used in fields such as material transportation, medical emergency response, and disaster relief. Especially in the scenario of medical material transportation, drones need to complete precise delivery in complex terrain or emergency situations. The landing safety of drones is directly related to the integrity of the transported materials (such as precision medical equipment) and the reliability of the drone itself.

[0003] Traditional solutions often employ mechanical structures such as springs, hydraulic shock absorbers, or flexible landing gear to absorb impact energy through deformation. However, such devices have limited buffering stroke and energy absorption capacity in high-speed forced landings or complex terrain (such as slopes or gravel ground), and mechanical components are prone to fatigue failure due to repeated impacts, resulting in low reliability. Summary of the Invention

[0004] The purpose of this section is to outline some aspects of embodiments of the present invention and to briefly describe some preferred embodiments. Simplifications or omissions may be made in this section, as well as in the abstract and title of this application, to avoid obscuring the purpose of these documents; however, such simplifications or omissions should not be construed as limiting the scope of the invention.

[0005] In view of the problems existing in the current drones, the present invention is proposed.

[0006] Therefore, the purpose of this invention is to provide a drone emergency landing device that incorporates an airbag. This device is suitable for solving the problem that traditional solutions often use mechanical structures such as springs, hydraulic shock absorbers, or elastic landing gear to absorb impact energy through deformation. However, such devices have limited buffering range and energy absorption capacity in high-speed emergency landings or complex terrain, and the mechanical components are prone to fatigue failure due to repeated impacts, resulting in low reliability.

[0007] To solve the above-mentioned technical problems, the present invention provides the following technical solution: a drone emergency landing device combined with an airbag, the drone emergency landing device comprising:

[0008] The main unit includes a drone body and fixed blocks symmetrically distributed on the outside of the drone body. Multiple sets of symmetrically distributed support columns are engaged and connected to the outer surface of the drone body.

[0009] The transport and placement unit includes a load-bearing base fixedly connected to one side of the lower surface of a support column and a holding plate fixedly connected to one side of the support column. A rotating groove is provided on one side of the load-bearing base. A connecting shaft is fixedly connected in the rotating groove. A blocking plate is rotatably connected to the outer surface of the connecting shaft. An air injection box is engaged and connected to the upper surface of the drone body.

[0010] The landing buffer unit includes a first buffer airbag housed in one side of the support column and a first one-way air inlet pipe opened in one side of the holding plate. An air storage chamber is opened in the holding plate, a second buffer airbag is installed in the load-bearing base, a third buffer airbag is installed in one side of the holding plate, and a first sealing film is fixedly connected in the air storage chamber.

[0011] As a preferred embodiment of the UAV forced landing device combined with airbag described in this invention, wherein: a fixed rod is fixedly connected to one side of the fixed block, a drive motor is fixedly connected to one end of the fixed rod, an inclined support rod is fixedly connected to one end of the drive motor near the fixed rod, a transmission block is fixedly connected to one end of the drive motor, and one end of the output shaft of the drive motor is rotatably connected to the output wheel through the internal structure of the transmission block, and an organic wing is fixedly connected to the outer surface of the output wheel.

[0012] As a preferred embodiment of the UAV forced landing device combined with airbags described in this invention, wherein: a rotating groove of the same size is provided on one side of the holding plate, an air guide groove is provided on one side of the load-bearing base, a placement groove is provided on the upper surface of the UAV body, and a fixing pipe is fixedly connected to the upper surface of the air injection box.

[0013] As a preferred embodiment of the UAV forced landing device with airbags described in this invention, wherein: an insertion rod is inserted and connected to one side of the support column, an L-shaped limiting rod is inserted and connected to the outer surface of one end of the insertion rod, a blocking plate is contacted on one side of the L-shaped limiting rod, symmetrically distributed L-shaped air slots are opened inside the UAV body, and symmetrically distributed connecting plates are fixedly connected to the upper surface of the load-bearing base and the holding plate.

[0014] As a preferred embodiment of the UAV forced landing device combined with airbags described in this invention, wherein: a fourth buffer airbag is provided in the placement slot, the fourth buffer airbag is connected to the inside of the air injection box through an L-shaped air groove, symmetrically distributed mounting plates are fixedly connected in the air storage chamber, and a first igniter is fixedly connected in the mounting plate.

[0015] As a preferred embodiment of the UAV forced landing device combined with airbags according to the present invention, the third buffer airbag and the air storage chamber are connected by a second one-way air inlet pipe, and the air intake direction of the second one-way air inlet pipe is from the air storage chamber to the third buffer airbag. A second sealing film is fixedly connected to the side of the second one-way air inlet pipe near the air storage chamber.

[0016] As a preferred embodiment of the UAV forced landing device combined with airbags described in this invention, wherein: the outer surface of the first igniter is sleeved inside the first sealing film, a small amount of flammable gas is filled between the first sealing film and the second sealing film, so that the flammable gas can quickly damage the first sealing film and the second sealing film under the action of the first igniter, the third buffer airbag is connected to the second buffer airbag through a gas guide groove, and the first buffer airbag and the third buffer airbag are directly connected.

[0017] As a preferred embodiment of the UAV forced landing device combined with airbags described in this invention, wherein: a telescopic protective frame is fixedly connected inside the air injection box, a force-bearing plate is fixedly connected to the lower surface of the telescopic protective frame, and multiple sets of equidistantly distributed connecting columns are fixedly connected to the upper surface of the force-bearing plate, and a first shape memory alloy traction rod and a second shape memory alloy traction rod are rotatably connected inside the connecting columns respectively.

[0018] As a preferred embodiment of the UAV forced landing device combined with airbag described in this invention, wherein: one end of the first shape memory alloy traction rod is fixedly connected to multiple sets of circumferentially distributed traction ropes, one end of each of the second shape memory alloy traction rods is fixedly connected to a buffer parachute, and one end of each traction rope is fixedly connected inside the buffer parachute.

[0019] As a preferred embodiment of the UAV forced landing device with airbags described in this invention, the first shape memory alloy tow bar, the second shape memory alloy tow bar, the tow rope and the buffer parachute can all be housed in a fixed tube, a second igniter is fixedly connected inside the gas injection box, the gas injection box is filled with flammable gas, and a third one-way air inlet pipe is fixedly connected to one side of the gas injection box, and exhaust valves are fixedly connected to the outer surfaces of the first buffer airbag, the second buffer airbag, the third buffer airbag and the fourth buffer airbag.

[0020] The beneficial effects of this invention are:

[0021] 1. By using the main body of the drone and its supporting components, the equipment can be quickly transported and placed by the drone during normal transportation. At the same time, the landing buffer unit is used to buffer and slow down the descent of the equipment.

[0022] 2. By using the arresting plate, load-bearing base, connecting plate, fixing pipe, air injection box and holding plate, the load-bearing base and holding plate can be placed on the bottom of the drone body, and then the drone's mobility can be used to quickly transport the medical device to the designated area. In addition, the airbag inside the landing buffer unit can provide protection to a certain extent during the drone's landing process.

[0023] 3. By utilizing the first buffer airbag, the fourth buffer airbag, the first one-way air intake pipe, the air storage chamber, the second buffer airbag, the third buffer airbag, and the exhaust valve, the equipment can reduce the impact force on the equipment when the drone lands and contacts the ground to a certain extent through multiple sets of airbags distributed in different areas of the equipment. At the same time, by utilizing the first and second igniters, the drone can quickly fill the airbags during the landing process and simultaneously eject the parachute built into the fixed tube, further improving the equipment's buffer landing effect through the parachute, thereby improving the equipment's buffer landing effect to a certain extent. Attached Figure Description

[0024] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the following description of the embodiments will be briefly introduced. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. Wherein:

[0025] Figure 1 This is a schematic diagram of the overall structure of a drone forced landing device combined with an airbag proposed in this invention;

[0026] Figure 2 This is a schematic diagram of the holding plate structure of a drone forced landing device combined with an airbag proposed in this invention;

[0027] Figure 3 This is a schematic cross-sectional view of the overall structure of a drone emergency landing device incorporating an airbag, as proposed in this invention.

[0028] Figure 4 This is a schematic diagram of the internal structure of the placement slot of a drone forced landing device combined with an airbag proposed in this invention;

[0029] Figure 5 This is a schematic diagram of the force plate structure of a drone forced landing device combined with an airbag proposed in this invention;

[0030] Figure 6 This is a schematic diagram of the structure of an airbag-integrated drone forced landing device proposed in this invention when the airbag is not deployed;

[0031] Figure 7 This is a schematic diagram of the deployment structure of the fourth and second buffer airbags of a drone forced landing device combined with airbags proposed in this invention.

[0032] Figure 8 This is a top view of the connecting plate of a drone emergency landing device incorporating an airbag, as proposed in this invention.

[0033] Figure 9This is a cross-sectional view of the load-bearing base of a drone forced landing device incorporating an airbag, as proposed in this invention.

[0034] Figure 10 This is a schematic diagram of the internal structure of the air storage chamber of a drone forced landing device combined with an airbag, as proposed in this invention.

[0035] Figure Descriptions: 100. Main Unit; 101. UAV Main Body; 102. Support Column; 103. Output Wheel; 104. Fixing Block; 105. Fixing Rod; 106. Tilt Support Rod; 107. Drive Motor; 108. Transmission Block; 109. Wing; 200. Transport and Placement Unit; 201. Barrier Plate; 202. Load-bearing Base; 203. Connecting Plate; 204. Fixing Pipe; 205. Air Injection Box; 206. Holding Plate; 207. Rotating Slot; 208. Connecting Shaft; 209. Insertion Rod; 210. Air Guide Slot; 211. L-shaped Limiting Rod; 212. Placement Slot; 213. L-shaped Air Slot; 300. Landing buffer unit; 301, first buffer airbag; 302, fourth buffer airbag; 303, first one-way air intake pipe; 304, air storage tank; 305, second buffer airbag; 306, third buffer airbag; 307, exhaust valve; 308, telescopic protective frame; 309, stress plate; 310, connecting column; 311, second shape memory alloy tow bar; 312, buffer parachute; 313, first shape memory alloy tow bar; 314, tow rope; 315, second one-way air intake pipe; 316, second sealing membrane; 317, first igniter; 318, first sealing membrane; 319, mounting plate; 320, second igniter. Detailed Implementation

[0036] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0037] Many specific details are set forth in the following description in order to provide a full understanding of the invention. However, the invention may also be practiced in other ways different from those described herein, and those skilled in the art can make similar extensions without departing from the spirit of the invention. Therefore, the invention is not limited to the specific embodiments disclosed below.

[0038] Secondly, the term "an embodiment" or "embodiment" as used herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the present invention. The phrase "in one embodiment" appearing in different places throughout this specification does not necessarily refer to the same embodiment, nor is it an embodiment that is mutually exclusive, either alone or selectively, with other embodiments.

[0039] Secondly, the present invention is described in detail with reference to the schematic diagrams. When detailing the embodiments of the present invention, for ease of explanation, the cross-sectional views illustrating the device structure may be partially enlarged, not according to the usual scale. Furthermore, the schematic diagrams are merely examples and should not limit the scope of protection of the present invention. In addition, actual fabrication should include three-dimensional spatial dimensions of length, width, and depth.

[0040] Example 1:

[0041] Reference Figure 1 - Figure 10 As an embodiment of the present invention, a drone forced landing device incorporating an airbag is provided, comprising a main body unit 100, a heating and holding unit 200, and a pressurization control unit 300.

[0042] The main unit 100 includes a drone body 101 and fixed blocks 104 symmetrically distributed on the outside of the drone body 101. Multiple sets of symmetrically distributed support columns 102 are engaged and connected to the outer surface of the drone body 101.

[0043] Furthermore, the transport and placement unit 200 includes a load-bearing base 202 fixedly connected to one side of the lower surface of the support column 102 and a holding plate 206 fixedly connected to one side of the support column 102. A rotating groove 207 is opened on one side of the load-bearing base 202. A connecting shaft 208 is fixedly connected in the rotating groove 207. A blocking plate 201 is rotatably connected to the outer surface of the connecting shaft 208. An air injection box 205 is engaged and connected to the upper surface of the drone body 101.

[0044] Finally, the landing buffer unit 300 includes a first buffer airbag 301 housed in one side of the support column 102 and a first one-way air inlet pipe 303 opened in one side of the holding plate 206. An air storage chamber 304 is opened in the holding plate 206, a second buffer airbag 305 is provided in the load-bearing base 202, a third buffer airbag 306 is provided in one side of the holding plate 206, and a first sealing film 318 is fixedly connected in the air storage chamber 304.

[0045] Furthermore, a fixing rod 105 is fixedly connected to one side of the fixing block 104, a drive motor 107 is fixedly connected to one end of the fixing rod 105, an inclined support rod 106 is fixedly connected to one end of the drive motor 107 near the fixing rod 105, a transmission block 108 is fixedly connected to one end of the drive motor 107, and one end of the output shaft of the drive motor 107 is rotatably connected to the output wheel 103 through the internal structure of the transmission block 108. An organic wing 109 is fixedly connected to the outer surface of the output wheel 103. The UAV body and its peripheral structure are all conventional components in the field of UAV technology, so their working principle will not be described in detail.

[0046] Furthermore, a rotating groove 207 of the same size is provided on one side of the holding plate 206, an air guide groove 210 is provided on one side of the load-bearing base 202, a placement groove 212 is provided on the upper surface of the drone body 101, and a fixing tube 204 is fixedly connected to the upper surface of the air injection box 205. The rotating groove 207 allows the barrier plate 201 on the upper surface of the holding plate 206 to be rotated, thereby allowing the medical device to be stored inside. At the same time, the fixing tube 204 is used to store the parachute inside. The interlocking support column 102 and the air injection box 205 allow for quick replacement and repair in case of damage, thereby improving the rapid installation effect of the equipment to a certain extent.

[0047] Furthermore, an insertion rod 209 is inserted and connected to one side of the support column 102, and an L-shaped limiting rod 211 is inserted and connected to the outer surface of one end of the insertion rod 209. A barrier plate 201 is in contact with one side of the L-shaped limiting rod 211. The UAV body 101 has symmetrically distributed L-shaped air grooves 213. The upper surfaces of the load-bearing base 202 and the holding plate 206 are both fixedly connected to symmetrically distributed connecting plates 203. The L-shaped limiting rod 211 and the insertion rod 209 cooperate with each other to quickly lock the barrier plate 201, thereby preventing the internal products from sliding out. At the same time, the L-shaped air groove 213 allows the gas drawn in during ignition in the gas injection box 205 to be quickly discharged into the fourth buffer airbag 302. A sealing film is also provided inside the L-shaped air groove 213.

[0048] Working principle:

[0049] By using the main body 101 of the drone and its supporting components, the transport and placement unit 200 and the landing buffer unit 300 can be quickly carried and processed by the drone during normal transportation. At the same time, the landing buffer unit 300 is used to buffer and slow down the landing of the equipment.

[0050] By utilizing the barrier plate 201, the load-bearing base 202, the connecting plate 203, the fixing pipe 204, the air injection box 205, and the holding plate 206, the load-bearing base 202 and the holding plate 206 can be used to place medical devices at the bottom of the UAV body 101, thereby utilizing the UAV's mobility to quickly transport the medical devices to the designated area, and to a certain extent, the airbag inside the landing buffer unit 300 can provide protection during the UAV's landing process.

[0051] By utilizing the first buffer airbag 301, the fourth buffer airbag 302, the first one-way air inlet pipe 303, the air storage chamber 304, the second buffer airbag 305, the third buffer airbag 306, and the exhaust valve 307, the equipment can reduce the impact force on the equipment when the drone lands and contacts the ground to a certain extent by using multiple sets of airbags distributed in different areas of the equipment. At the same time, by using the first igniter 317 and the second igniter 320, the drone can quickly fill the airbags during the landing process and simultaneously eject the parachute built into the fixed pipe 204, further improving the buffer landing effect of the equipment through the parachute, thereby improving the buffer landing effect of the equipment to a certain extent.

[0052] Example 2:

[0053] Reference Figure 3 and Figure 5 as well as Figure 7 and Figure 10 The difference from Embodiment 1 is that a fourth buffer airbag 302 is provided in the placement slot 212. The fourth buffer airbag 302 is connected to the inside of the gas injection box 205 through the L-shaped gas slot 213. A symmetrically distributed mounting plate 319 is fixedly connected in the gas storage chamber 304. A first igniter 317 is fixedly connected in the mounting plate 319. The fourth buffer airbag 302 is inflated and unfolded in an L-shaped structure. The gas storage chamber 304 can be filled with a large amount of compressed nitrogen. The combustible gas is then ignited by the igniter, which damages the sealing film, allowing nitrogen to rush into the airbag. The impact force of the combustible gas explosion can be used to push the parachute out of the fixing tube 204.

[0054] Furthermore, the third buffer airbag 306 and the air storage chamber 304 are connected by a second one-way air inlet pipe 315, and the air intake direction of the second one-way air inlet pipe 315 is from the air storage chamber 304 to the third buffer airbag 306. A second sealing membrane 316 is fixedly connected to the side of the second one-way air inlet pipe 315 near the air storage chamber 304. The one-way air inlet pipe prevents the gas inside the air storage chamber 304 and the airbag from overflowing outwards, while allowing external air to flow into the air storage chamber 304 or the airbag in one direction, thereby quickly drawing the external air inwards through the pressure difference.

[0055] Furthermore, the outer surface of the first igniter 317 is fitted inside the first sealing film 318, and a small amount of flammable gas is filled between the first sealing film 318 and the second sealing film 316, so that the flammable gas can quickly damage the first sealing film 318 and the second sealing film 316 under the action of the first igniter 317. The third buffer airbag 306 and the second buffer airbag 305 are connected through the air guide groove 210. The first buffer airbag 301 and the third buffer airbag 306 are directly connected. The second buffer airbag 305 is concave after being inflated. During the deployment of the fourth buffer airbag 302 and the second buffer airbag 305, the first buffer airbag 301 is deployed from one side of the support column 102, thereby separating the other two sets of buffer airbags during the deployment process, thus avoiding the buffer airbags from touching the wing 109 to a certain extent.

[0056] Furthermore, a telescopic protective frame 308 is fixedly connected inside the air injection box 205. A force-bearing plate 309 is fixedly connected to the lower surface of the telescopic protective frame 308. Multiple sets of equidistantly distributed connecting columns 310 are fixedly connected to the upper surface of the force-bearing plate 309. A first shape memory alloy traction rod 313 and a second shape memory alloy traction rod 311 are rotatably connected inside the connecting columns 310. Multiple sets of circumferentially distributed traction ropes 314 are fixedly connected to one end of the first shape memory alloy traction rod 313. A buffer parachute 312 is fixedly connected to one end of each of the second shape memory alloy traction rods 311. One end of the traction rope 314 is fixedly connected inside the buffer parachute 312. The shape memory alloy traction rods can be stored inside the fixed tube 204. When the shape memory alloy traction rods are extended, they can be unfolded from the outside. The hardness during unfolding reduces the likelihood of the traction rods coiling up after the parachute is unfolded.

[0057] Furthermore, the first shape memory alloy traction rod 313, the second shape memory alloy traction rod 311, the traction rope 314, and the buffer parachute 312 can all be housed in the fixing tube 204. A second igniter 320 is fixedly connected inside the gas injection box 205. The gas injection box 205 is filled with flammable gas, and a third one-way air inlet pipe is fixedly connected to one side of the gas injection box 205. Exhaust valves 307 are fixedly connected to the outer surfaces of the first buffer airbag 301, the second buffer airbag 305, the third buffer airbag 306, and the fourth buffer airbag 302.

[0058] Working principle: First, through the synergistic effect of the four-stage buffer airbag system and the shape memory alloy parachute device, energy absorption in stages is achieved under high-speed forced landing and complex terrain: the first to fourth buffer airbags 302 deploy in layers to form a three-dimensional buffer network; the shape memory alloy tow bar quickly pops open the parachute to reduce vertical impact; the igniter ignites the gas to break through the sealing film and achieves millisecond-level airbag inflation.

[0059] Secondly, the holding plate 206 and the load-bearing base 202 form a closed cavity for placing medical devices. The L-shaped limiting rod 211 locks the barrier plate 201 to prevent items from slipping during transportation. The insertion rod 209 reinforces the connection between the support column 102 and the base to ensure overall rigidity. The air injection box 205 has a built-in folding buffer parachute 312, and the fixing tube 204 serves as the parachute compartment. The parachute body is connected to the memory alloy traction rod via the traction rope 314. At the same time, the first buffer airbag 301 unfolds from the side of the support column 102 to isolate the wing 109 area. The second buffer airbag 305 has a concave structure that wraps around the bottom surface of the load-bearing base 202 to absorb ground impact. The third buffer airbag 306 is connected to the second airbag through the air guide groove 210 to expand the buffer area. The fourth buffer airbag 302 has an L-shaped structure that covers the top of the drone to prevent rollover damage.

[0060] Secondly, the igniter ignites the flammable gas inside the gas injection box 205. The gas expands and breaks through the sealing membrane, releasing compressed nitrogen from the gas storage chamber 304. The nitrogen is injected into the airbag through the one-way inlet pipe, thus quickly completing the inflation. The exhaust valve 307 on the surface of the airbag releases the internal gas when under pressure to avoid rebound impact. The deflagration of the gas injection box 205 pushes the force plate 309, compresses the telescopic protective frame 308, and transmits the thrust to the connecting column 310, releasing the first shape memory alloy traction rod 313. The traction rod unfolds instantly when heated, pulling out the buffer parachute 312. The second shape memory alloy traction rod 311 unfolds and hardens simultaneously to keep the parachute ropes taut. The circumferential distribution design of the dual traction rods eliminates the risk of parachute rope entanglement.

[0061] Finally, at the moment the drone stalls, the fuselage sensors activate the igniter. The first igniter 317 ignites the flammable gas in the gas storage chamber 304, which breaks through the first sealing membrane 318, injecting nitrogen into the fourth buffer airbag 302 to form top protection. The airflow triggers the second igniter 320 through the L-shaped gas groove 213, which breaks through the second sealing membrane 316, and nitrogen is injected into the third buffer airbag 306 through the second one-way air inlet pipe 315. The third airbag supplies gas to the second buffer airbag 305 through the gas guide groove 210. The first buffer airbag 301 deploys laterally from the support column 102. At the same time as the gas injection box 205 explodes, the gas pushes the force plate 309, which in turn compresses the telescopic protective frame 308, causing it to release the shape memory alloy traction rod. The traction rod is heated and unfolds, pulling out the buffer parachute 312, thereby reducing the kinetic energy of the fall during the forced landing to a certain extent.

[0062] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. A drone emergency landing device incorporating an airbag, characterized in that, The drone forced landing device includes: The main body unit (100) includes a drone body (101) and fixed blocks (104) symmetrically distributed on the outside of the drone body (101). Multiple sets of symmetrically distributed support columns (102) are engaged and connected to the outer surface of the drone body (101). The transport and placement unit (200) includes a load-bearing base (202) fixedly connected to one side of the lower surface of the support column (102) and a holding plate (206) fixedly connected to one side of the support column (102). A rotating groove (207) is provided on one side of the load-bearing base (202). A connecting shaft (208) is fixedly connected in the rotating groove (207). A blocking plate (201) is rotatably connected to the outer surface of the connecting shaft (208). An air injection box (205) is engaged with the upper surface of the drone body (101). The landing buffer unit (300) includes a first buffer airbag (301) housed in one side of the support column (102) and a first one-way air inlet pipe (303) opened on one side of the holding plate (206). An air storage chamber (304) is opened in the holding plate (206), a second buffer airbag (305) is provided in the load-bearing base (202), a third buffer airbag (306) is provided on one side of the holding plate (206), and a first sealing film (318) is fixedly connected in the air storage chamber (304). The holding plate (206) has a rotating groove (207) of the same size on one side, the load-bearing base (202) has an air guide groove (210) on one side, the drone body (101) has a placement groove (212) on the upper surface, and the air injection box (205) has a fixed pipe (204) fixedly connected to the upper surface. The placement slot (212) is provided with a fourth buffer airbag (302), which is connected to the inside of the gas injection box (205) through an L-shaped air slot (213). The gas storage chamber (304) is fixedly connected with symmetrically distributed mounting plates (319), and the mounting plates (319) are fixedly connected with a first igniter (317). The third buffer airbag (306) and the air storage chamber (304) are connected by a second one-way air inlet pipe (315), and the air inlet direction of the second one-way air inlet pipe (315) is from the air storage chamber (304) to the third buffer airbag (306). A second sealing film (316) is fixedly connected to the side of the second one-way air inlet pipe (315) near the air storage chamber (304). The outer surface of the first igniter (317) is fitted inside the first sealing film (318). A small amount of flammable gas is filled between the first sealing film (318) and the second sealing film (316), so that the flammable gas can quickly damage the first sealing film (318) and the second sealing film (316) under the action of the first igniter (317). The third buffer airbag (306) is connected to the second buffer airbag (305) through the gas guide groove (210). The first buffer airbag (301) and the third buffer airbag (306) are directly connected.

2. The UAV forced landing device combined with an airbag according to claim 1, characterized in that: A fixing rod (105) is fixedly connected to one side of the fixing block (104). A drive motor (107) is fixedly connected to one end of the fixing rod (105). An inclined support rod (106) is fixedly connected to one end of the drive motor (107) near the fixing rod (105). A transmission block (108) is fixedly connected to one end of the drive motor (107). One end of the output shaft of the drive motor (107) is rotatably connected to the output wheel (103) through the internal structure of the transmission block (108). An organic wing (109) is fixedly connected to the outer surface of the output wheel (103).

3. The UAV forced landing device combined with an airbag according to claim 1, characterized in that: An insertion rod (209) is inserted and connected to one side of the support column (102). An L-shaped limiting rod (211) is inserted and connected to the outer surface of one end of the insertion rod (209). A barrier plate (201) is in contact with one side of the L-shaped limiting rod (211). A symmetrically distributed L-shaped air groove (213) is opened inside the main body (101) of the drone. A symmetrically distributed connecting plate (203) is fixedly connected to the upper surface of the load-bearing base (202) and the holding plate (206).

4. The UAV forced landing device combined with an airbag according to claim 1, characterized in that: The gas injection box (205) is fixedly connected to a telescopic protective frame (308), and a force plate (309) is fixedly connected to the lower surface of the telescopic protective frame (308). Multiple sets of equidistant connecting columns (310) are fixedly connected to the upper surface of the force plate (309), and a first memory alloy traction rod (313) and a second memory alloy traction rod (311) are rotatably connected in the connecting columns (310).

5. A drone forced landing device incorporating an airbag according to claim 4, characterized in that: One end of the first shape memory alloy traction rod (313) is fixedly connected to multiple sets of circumferentially distributed traction ropes (314), and one end of the second shape memory alloy traction rod (311) is fixedly connected to a buffer parachute (312), and one end of the traction rope (314) is fixedly connected inside the buffer parachute (312).

6. The UAV forced landing device combined with an airbag according to claim 5, characterized in that: The first shape memory alloy traction rod (313), the second shape memory alloy traction rod (311), the traction rope (314) and the buffer parachute (312) can all be stored in the fixed tube (204). The second igniter (320) is fixedly connected in the gas injection box (205). The gas injection box (205) is filled with flammable gas, and a third one-way air inlet pipe is fixedly connected to one side of the gas injection box (205). The first buffer airbag (301), the second buffer airbag (305), the third buffer airbag (306) and the fourth buffer airbag (302) are all fixedly connected with exhaust valves (307).

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