An emergency air cushion soft landing device for unmanned aerial vehicles

Abstract

The present application relates to the technical field of unmanned aerial vehicle, especially to an emergency air cushion soft landing device for unmanned aerial vehicle. The device comprises a frame, a triggering mechanism, a locking mechanism, an inflation mechanism and an air cushion. The high-pressure gas cylinder of the inflation mechanism is arranged on the frame. The piercing member is slidable to pierce the sealing diaphragm of the high-pressure gas cylinder under the drive of the energy storage member. The locking mechanism is used to lock the piercing member in the safe state. The triggering mechanism is used to sense the change of air pressure caused by the falling of the unmanned aerial vehicle and control the locking mechanism to release the piercing member. The injection booster is arranged at the air outlet end of the piercing member and contains a mixing chamber and a one-way valve inside. After the piercing member pierces the diaphragm, the high-pressure gas in the high-pressure gas cylinder is sprayed into the mixing chamber at high speed to form a low-pressure area. The outside air is sucked in through the one-way valve and is quickly inflated into the bottom air cushion after mixing. The injection booster is used to improve the inflation speed and amount of the air cushion, realize large-capacity inflation under the limited gas source and ensure that the air cushion is fully expanded in the falling moment.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and more particularly to an emergency air cushion soft landing device for UAVs. Background Technology

[0002] During flight, drones may encounter emergencies such as power failure, control malfunction, or sudden severe weather, causing them to crash out of control. If effective cushioning and protection measures are not taken in time, a hard landing or crash of a drone can cause severe damage to the aircraft, destruction of expensive onboard equipment, and may even pose a serious threat to the safety of people and property on the ground.

[0003] Currently, most common emergency protection devices for drones use parachutes or airbags for cushioning. However, existing airbag cushioning devices usually rely on high-pressure gas cylinders for direct inflation. In a limited space, the amount of gas stored in the high-pressure gas cylinder is insufficient to quickly inflate a large-volume airbag, resulting in insufficient cushioning effect. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to solve at least one of the technical problems mentioned above.

[0005] The solution to the technical problem of this invention is: an emergency air cushion soft landing device for unmanned aerial vehicles (UAVs), comprising a frame, a triggering mechanism, a locking mechanism, an inflation mechanism, and an air cushion. The inflation mechanism includes a high-pressure gas cylinder, an energy storage device, a puncture device, and an ejector pressurization device. The high-pressure gas cylinder is mounted on the frame, and its opening is provided with a sealing diaphragm. The puncture device is slidably mounted on the frame in a direction toward the opening of the high-pressure gas cylinder to puncture the sealing diaphragm. The puncture device has a gas channel connecting its two ends. The energy storage device is mounted on the frame, and its two ends respectively abut against the frame and the puncture device. The energy storage device has a tendency to move the puncture device toward the opening of the high-pressure gas cylinder. The locking mechanism... The locking mechanism, mounted on the frame, is releasably engaged with the puncture member to restrict its movement. A triggering mechanism, also mounted on the frame and signal-connected to the locking mechanism, controls the locking mechanism to release its engagement with the puncture member. The ejector pressurizing component includes a cavity and a one-way valve. The cavity is located at the end of the puncture member furthest from the high-pressure gas cylinder. Inside the cavity is a mixing chamber. The cavity also has an inlet sealed to the outlet of the gas channel, an outlet connected to the air cushion, and at least one intake port connecting the mixing chamber to the external environment. The one-way valve is located at the intake port to prevent backflow of gas from the mixing chamber to the external environment. The air cushion is located at the bottom of the frame.

[0006] As a further improvement to the above technical solution, the air outlet end of the puncture member extends into the mixing chamber, and the air outlet end of the gas channel faces the air outlet. A gap is left between the outer peripheral wall of the air outlet end of the puncture member and the inner wall of the mixing chamber. The gap is connected to the air inlet. The outer diameter of the outer peripheral wall of the air outlet end of the puncture member gradually decreases along the airflow direction.

[0007] As a further improvement to the above technical solution, the cross-sectional area of ​​the gas channel gradually decreases along the airflow direction.

[0008] As a further improvement to the above technical solution, the air inlet is threadedly sealed to the outer wall of the puncture component, the air outlet is provided with an outwardly extending connecting part, and the air cushion is connected to the connecting part through a flexible pipe.

[0009] As a further improvement to the above technical solution, the one-way valve includes a valve stem, an elastic element, and a sealing disc disposed at one end of the valve stem. The valve stem is slidably disposed on the cavity along the axial direction of the air intake. The sealing disc is located inside the mixing cavity. The elastic element is sleeved on the valve stem. The two ends of the elastic element abut against the cavity and the sealing disc, respectively. The elastic element has a tendency to move the sealing disc toward the air intake.

[0010] As a further improvement to the above technical solution, the triggering mechanism includes a housing, an air collecting pipe, a pressure-sensing diaphragm, and a micro switch. The housing is disposed at the bottom of the frame. The pressure-sensing diaphragm is sealed on the inner wall of the housing and divides the interior of the housing into a pressure-sensing chamber and an installation chamber. The housing has a vent hole at the position corresponding to the pressure-sensing chamber. The air collecting pipe is disposed at the bottom of the frame, with its input end facing downwards to receive the oncoming airflow when the drone falls. The output end of the air collecting pipe is sealed and connected to the vent hole. The micro switch is disposed in the installation chamber, with its trigger end opposite to the pressure-sensing diaphragm, so that the pressure-sensing diaphragm deforms and presses the trigger end when the air pressure in the pressure-sensing chamber reaches a set value. The micro switch is electrically connected to the locking mechanism.

[0011] As a further improvement to the above technical solution, the inlet end of the gas collecting pipe is shaped like an inverted funnel, and the diameter of the inlet end of the gas collecting pipe gradually increases from top to bottom.

[0012] As a further improvement to the above technical solution, the locking mechanism includes a driving device and a locking push rod. The locking push rod is slidably mounted on the frame, and the sliding direction of the locking push rod intersects with the sliding direction of the puncturing member. One end of the locking push rod is provided with a fastening part, and the outer wall of the puncturing member is provided with a slot adapted to the fastening part. The driving device is mounted on the frame and electrically connected to the triggering mechanism. The driving device is used to drive the locking push rod to slide so that the fastening part disengages from the slot.

[0013] As a further improvement to the above technical solution, a buffer assembly is also included. The air cushion is disposed at the bottom of the frame via the buffer assembly. The buffer assembly includes a cylinder, a first push rod, a first pressure plate, a second push rod, a second pressure plate, a first energy-absorbing block, and a second energy-absorbing block. The cylinder is disposed at the bottom of the frame and is a hollow cylindrical structure with a downward opening. The first pressure plate is slidably disposed within the cylinder. The first energy-absorbing block abuts against the inner top wall of the cylinder and the upper surface of the first pressure plate. The first push rod is vertically disposed on the lower surface of the first pressure plate. The second pressure plate is slidably disposed within the cylinder and located at... Below the first pressure plate, the second energy-absorbing block is sleeved on the outside of the first push rod and abuts between the lower surface of the first pressure plate and the upper surface of the second pressure plate. The second push rod is fixed vertically to the lower surface of the second pressure plate. The second push rod is a hollow tubular structure. The first push rod is coaxial and slidably inserted inside the second push rod. A mounting block is provided at the end of the second push rod away from the second pressure plate. The air cushion is disposed on the lower surface of the mounting block. The bottom end of the first push rod and the upper surface of the mounting block are spaced apart to form a clearance gap. The height of the clearance gap is greater than or equal to the maximum compression thickness of the second energy-absorbing block.

[0014] As a further improvement to the above technical solution, both the first energy-absorbing block and the second energy-absorbing block are metal honeycomb structures, which are used to deform under pressure to absorb impact energy. The stiffness of the first energy-absorbing block is greater than that of the second energy-absorbing block.

[0015] The beneficial effects of this invention are as follows: the frame provides the mounting base and is fixedly connected to the drone fuselage; the triggering mechanism monitors the drone's fall status and sends signals; the locking mechanism locks the puncture component and releases the lock after receiving a signal from the triggering mechanism; the high-pressure gas cylinder provides the initial power source for inflation; the energy storage component provides the mechanical energy to drive the puncture component; the puncture component punctures the gas cylinder's sealing diaphragm to release gas; the ejector pressurization component amplifies the inflation flow; and the air cushion absorbs the physical impact of the drone hitting the ground. Through the ejector pressurization structure, when the puncture component punctures the sealing diaphragm, the high-pressure gas in the high-pressure gas cylinder is injected into the mixing chamber through the gas channel to form a local low-pressure zone, thereby drawing in a large amount of outside air through the intake port, mixing it with the high-pressure gas, and then inflating the air cushion through the outlet. This improves the inflation speed and volume of the air cushion, ensuring that the air cushion fully expands and deploys in a very short time during the drone's descent, providing reliable and sufficient cushioning protection for the drone and increasing the success rate of soft landing. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the overall structure of one embodiment of the present invention.

[0017] Figure 2 This is a schematic diagram of the ejector booster component according to one embodiment of the present invention.

[0018] Figure 3 This is a schematic diagram of the locking mechanism and inflation mechanism according to one embodiment of the present invention.

[0019] Figure 4 This is a schematic diagram of the triggering mechanism according to one embodiment of the present invention.

[0020] Figure 5 This is a schematic diagram of the structure of a buffer component according to one embodiment of the present invention.

[0021] Reference numerals in the attached drawings: 100-frame, 200-trigger mechanism, 210-box, 211-pressure sensing chamber, 212-mounting chamber, 213-vent, 220-gas collecting pipe, 230-pressure sensing diaphragm, 240-micro switch, 300-locking mechanism, 310-drive device, 320-locking push rod, 321-fastening part, 330-slot, 400-inflation mechanism, 410-high-pressure gas cylinder, 411-sealing diaphragm, 420-energy storage element, 430-puncture element, 431-gas passage, 432-slot, 44 0-Ejector pressurization component, 441-Cavity, 442-Mixing chamber, 443-Inlet, 444-Outlet, 445-Inlet, 446-One-way valve, 4461-Valve stem, 4462-Elastic element, 4463-Sealing disc, 447-Connecting part, 500-Air cushion, 600-Buffer assembly, 610-Cylinder, 620-First push rod, 630-First pressure plate, 640-Second push rod, 650-Second pressure plate, 660-First energy-absorbing block, 670-Second energy-absorbing block, 680-Mounting block, 690-Clearance clearance. Detailed Implementation

[0022] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments have been briefly explained above. Obviously, the described drawings are only a part of the embodiments of the present invention, and not all of them. Those skilled in the art can obtain other design schemes and drawings based on these drawings without creative effort.

[0023] The following will clearly and completely describe the concept, specific structure, and technical effects of the present invention in conjunction with embodiments and accompanying drawings, so as to fully understand the purpose, features, and effects of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, not all of them. Other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are all within the scope of protection of the present invention. Furthermore, all connections / linkages mentioned herein do not simply refer to direct connection of components, but rather to the ability to form a better connection structure by adding or reducing connecting accessories according to specific implementation conditions. The various technical features in this invention can be combined interactively without contradicting each other.

[0024] In current emergency air cushion protection devices for drones, the inflation system typically relies solely on the limited compressed gas in the gas cylinder for direct inflation. However, when a drone experiences a sudden malfunction and falls out of control, the system has extremely short operating time. Traditional direct inflation methods have limited flow, preventing the air cushion from filling to a large volume in an instant. As a result, the air cushion may not fully inflate the drone before it hits the ground, failing to provide the necessary cushioning and soft landing.

[0025] Therefore, this invention proposes an emergency air cushion soft landing device for unmanned aerial vehicles (UAVs), referring to... Figures 1-5 It includes a frame 100, a triggering mechanism 200, a locking mechanism 300, an inflation mechanism 400, and an air cushion 500. The inflation mechanism 400 includes a high-pressure gas cylinder 410, an energy storage component 420, a puncture component 430, and an ejector pressurization component 440. The high-pressure gas cylinder 410 is mounted on the frame 100, and the cylinder opening of the high-pressure gas cylinder 410 is provided with a sealing diaphragm 411. The puncture component 430 is slidably mounted on the frame 100 in the direction toward the cylinder opening of the high-pressure gas cylinder 410. On the frame 100, a gas channel 431 is provided inside the piercing member 430 to puncture the sealing diaphragm 411. The energy storage member 420 is disposed on the frame 100, and its two ends abut against the frame 100 and the piercing member 430, respectively. The energy storage member 420 has a tendency to move the piercing member 430 toward the mouth of the high-pressure gas cylinder 410. The locking mechanism 300 is disposed on the frame 100. Mechanism 300 is releasably engaged with the puncture member 430 to restrict the movement of the puncture member 430. Trigger mechanism 200 is mounted on the frame 100 and signal-connected to the locking mechanism 300 to control the locking mechanism 300 to release the engagement with the puncture member 430. The ejector pressurization member 440 includes a cavity 441 and a one-way valve 446. The cavity 441 is located at the end of the puncture member 430 away from the high-pressure gas cylinder 410. The body 441 has a mixing chamber 442 inside. The chamber 441 is also provided with an air inlet 443 that is sealed and connected to the air outlet of the gas channel 431, an air outlet 444 that is connected to the air cushion 500, and at least one air intake 445 that connects the mixing chamber 442 to the external environment. The one-way valve 446 is provided at the air intake 445 to prevent the gas in the mixing chamber 442 from flowing back to the external environment. The air cushion 500 is provided at the bottom of the frame 100.

[0026] The frame 100 provides the mounting base and is fixed to the drone fuselage; the triggering mechanism 200 monitors the drone's fall status and sends signals; the locking mechanism 300 locks the puncture component 430 and releases the lock after receiving a signal from the triggering mechanism 200; the high-pressure gas cylinder 410 provides the initial power source for inflation; the energy storage component 420 provides the mechanical energy to drive the movement of the puncture component 430; the puncture component 430 is used to puncture the gas cylinder sealing diaphragm 411 to release gas; the ejector pressurization component 440 is used to amplify the inflation flow; and the air cushion 500 is used to absorb the physical impact of the drone hitting the ground. Through the ejector pressurization structure, when the puncture component 430 punctures the sealing diaphragm 411, the high-pressure gas in the high-pressure gas cylinder 410 is injected into the mixing chamber 442 through the gas channel 431 to form a local low-pressure area, thereby drawing in a large amount of outside air through the intake port 445, mixing it with the high-pressure gas, and then filling the air cushion 500 through the outlet port 444. The inflation speed and inflation volume of the air cushion 500 have been improved, ensuring that the air cushion 500 fully expands and deploys in a very short time during the drone's descent, providing reliable and sufficient cushioning protection for the aircraft and improving the success rate of soft landing.

[0027] The workflow is as follows: When the drone suddenly crashes, the triggering mechanism 200 detects the abnormality and sends a signal to the locking mechanism 300; the locking mechanism 300 activates, releasing the clamping constraint on the piercing component 430; the energy storage component 420 releases energy to drive the piercing component 430 to move and pierce the sealing diaphragm 411 of the high-pressure gas cylinder 410; the high-pressure gas in the high-pressure gas cylinder 410 is injected along the gas channel 431 into the mixing chamber 442 of the ejector pressurizer 440, forming a local low-pressure area in the mixing chamber 442; the outside air, under the action of pressure difference, opens the one-way valve 446, rushes into the mixing chamber 442 through the air intake 445, quickly mixes with the original high-pressure gas, and then rushes into the air cushion 500 at the bottom through the air outlet 444; the air cushion 500 fully expands in a very short time, and when the drone touches the ground, the air cushion 500 is compressed and deformed to absorb kinetic energy, completing the safe soft landing of the drone.

[0028] In one embodiment, the outlet end of the puncture member 430 extends into the mixing chamber 442, and the outlet end of the gas channel 431 faces the outlet 444. A gap is left between the outer peripheral wall of the outlet end of the puncture member 430 and the inner wall of the mixing chamber 442, and the gap is connected to the intake port 445. The outer diameter of the outer peripheral wall of the outlet end of the puncture member 430 gradually decreases along the airflow direction. When a high-speed airflow is ejected from the outlet end of the puncture member 430, a low-pressure zone is generated in the gap between its outer peripheral wall and the inner wall of the mixing chamber 442, thereby continuously drawing in outside air and achieving efficient gas mixing and pressurization; the tapered shape helps to reduce flow resistance and improve ejection efficiency.

[0029] When high-pressure gas enters the mixing chamber 442 from the outlet of the airflow channel, the flow rate may be insufficient, resulting in poor ejection effect and difficulty in drawing in a sufficient amount of outside air in a short time. Therefore, in one embodiment, the cross-sectional area of ​​the gas channel 431 gradually decreases along the airflow direction. The gradually decreasing cross-section can accelerate the flow, allowing the gas flowing out of the high-pressure gas cylinder 410 to reach a higher jet velocity at the outlet, thereby creating a stronger negative pressure area in the mixing chamber 442 and enhancing the ability to draw in outside air.

[0030] High-pressure gas may leak during transmission, wasting gas and reducing the injection pressure in the mixing chamber 442, thus affecting the inflation effect of the air cushion 500. Therefore, in one embodiment, the air inlet 443 is threadedly sealed to the outer wall of the puncture member 430, and the air outlet 444 is provided with an outwardly extending connecting portion 447. The air cushion 500 is connected to the connecting portion 447 through a flexible pipe. The threaded sealing connection ensures the airtightness and structural strength of the air inlet under high-pressure conditions; the flexible pipe not only facilitates the folding and storage of the air cushion 500, but also provides flexible cushioning during inflation and impact, preventing the interface from breaking and leaking due to excessive instantaneous stress.

[0031] After inflation is complete or when the air cushion 500 deforms due to the weight of the drone, if the air intake 445 cannot be closed in time, the gas in the mixing chamber 442 will backflow and leak outward, causing the air cushion 500 to collapse and fail instantly. Therefore, in one embodiment, the one-way valve 446 includes a valve stem 4461, an elastic element 4462, and a sealing disc 4463 disposed at one end of the valve stem 4461. The valve stem 4461 is slidably disposed on the cavity 441 along the axial direction of the air intake 445. The sealing disc 4463 is located inside the mixing chamber 442. The elastic element 4462 is sleeved on the valve stem 4461. The two ends of the elastic element 4462 abut against the cavity 441 and the sealing disc 4463, respectively. The elastic element 4462 has a tendency to move the sealing disc 4463 towards the air intake 445. When high-speed gas enters and creates a local low-pressure area in the mixing chamber 442, the external air pressure can overcome the pre-tightening force of the elastic element 4462 and push the sealing disc 4463 to move inward to the mixing chamber 442 to open the air intake port 445. When the pressure in the mixing chamber 442 rises or is higher than that in the outside, the elastic element 4462 pushes the sealing disc 4463 to reset, sealing the air intake port 445, preventing gas backflow, and ensuring that the air cushion 500 maintains pressure.

[0032] Traditional electronic gravity sensors or attitude sensors are prone to response delays or misjudgments under complex electromagnetic environments or special airflow interference, potentially missing the optimal inflation time. Therefore, in one embodiment, the triggering mechanism 200 includes a housing 210, an air collection pipe 220, a pressure-sensing diaphragm 230, and a microswitch 240. The housing 210 is disposed at the bottom of the frame 100. The pressure-sensing diaphragm 230 is sealed on the inner wall of the housing 210, dividing the interior of the housing 210 into a pressure-sensing chamber 211 and an installation chamber 212. The housing 210 has a vent 213 corresponding to the pressure-sensing chamber 211. The air collection pipe 220 is disposed at the bottom of the frame 100. The input end of the air collecting pipe 220 is positioned downwards to catch the oncoming airflow when the drone falls. The output end of the air collecting pipe 220 is sealed and connected to the vent 213. The micro switch 240 is disposed inside the mounting chamber 212. The trigger end of the micro switch 240 is positioned opposite the pressure-sensitive diaphragm 230, so that the pressure-sensitive diaphragm 230 deforms and presses the trigger end when the air pressure in the pressure-sensitive chamber 211 reaches a set value. The micro switch 240 is electrically connected to the locking mechanism 300. Utilizing the dynamic air pressure changes caused by the intense oncoming airflow generated during the drone's descent, the pressure-sensitive diaphragm 230 deforms instantaneously to trigger the micro switch 240 when the air pressure reaches the fall threshold, resulting in rapid response and extremely strong anti-interference capability. Preferably, multiple triggering mechanisms 200 can be set, and the input ends of the air collection pipes 220 of the multiple triggering mechanisms 200 are set in different directions so that the air pressure changes in different directions can still be effectively collected when the UAV tilts to the side, ensuring reliable triggering.

[0033] If the oncoming airflow intensity cannot be effectively converged during free fall, the pressure change may be insignificant, resulting in a sluggish triggering. Therefore, in one embodiment, the input end of the air collecting pipe 220 is shaped like an inverted funnel, and the diameter of the input end of the air collecting pipe 220 gradually increases from top to bottom. The inverted funnel-shaped flared design can catch and converge the oncoming airflow during fall over a larger area, and achieve pressure amplification gain through the reduction of the cross-section, further improving the triggering sensitivity of the pressure-sensitive diaphragm 230.

[0034] If the locking mechanism 300 has a complex structure or a slow response, the puncture member 430 may not be released in time, delaying inflation and affecting the emergency protection effect. Therefore, in one embodiment, the locking mechanism 300 includes a driving device 310 and a locking push rod 320. The locking push rod 320 is slidably mounted on the frame 100, and the sliding direction of the locking push rod 320 intersects the sliding direction of the puncture member 430. One end of the locking push rod 320 is provided with a fastening part 321, and the outer wall of the puncture member 430 is provided with a slot 330 adapted to the fastening part 321. The driving device 310 is mounted on the frame 100 and is electrically connected to the triggering mechanism 200. The driving device 310 is used to drive the locking push rod 320 to slide so that the fastening part 321 disengages from the slot 330. The drive device 310 can be a linear drive device 310 such as a linear cylinder or a gear rack device. The drive device 310 drives the locking push rod 320 to perform a linear pulling motion to disengage the fastening part 321. The mechanical action path is short, there is no complex linkage mechanism, the structure is simple and reliable, and the response is rapid.

[0035] Relying solely on the air cushion 500 for cushioning is insufficient when the drone has a large mass or falls at a high speed; the air cushion 500 may be crushed instantly, resulting in limited cushioning effectiveness. Therefore, in one embodiment, a cushioning assembly 600 is also included. The air cushion 500 is disposed at the bottom of the frame 100 via the cushioning assembly 600. The cushioning assembly 600 includes a cylinder 610, a first push rod 620, a first pressure plate 630, a second push rod 640, a second pressure plate 650, a first energy-absorbing block 660, and a second energy-absorbing block 670. The cylinder 610 is disposed at the bottom of the frame 100 and is a hollow cylindrical structure with a downward opening. The first pressure plate 630 is slidably disposed within the cylinder 610. The first energy-absorbing block 660 abuts against the inner top wall of the cylinder 610 and the upper surface of the first pressure plate 630. The first push rod 620 is vertically disposed on the lower surface of the first pressure plate 630. The second pressure plate 650 is slidably disposed within the cylinder 610. The first push rod 670 is located below the first pressure plate 630. The second energy-absorbing block 670 is sleeved on the outside of the first push rod 620 and abuts between the lower surface of the first pressure plate 630 and the upper surface of the second pressure plate 650. The second push rod 640 is fixed vertically to the lower surface of the second pressure plate 650. The second push rod 640 is a hollow tubular structure. The first push rod 620 is coaxially and slidably inserted inside the second push rod 640. The end of the second push rod 640 away from the second pressure plate 650 is provided with a mounting block 680. The air cushion 500 is disposed on the lower surface of the mounting block 680. The bottom end of the first push rod 620 and the upper surface of the mounting block 680 form a clearance gap 690. The height of the clearance gap 690 is greater than or equal to the maximum compression thickness of the second energy-absorbing block 670. When subjected to a small impact load, the second energy-absorbing block 670 is compressed and deformed to absorb energy. That is, the air cushion 500 pushes the second push rod 640, and the second pressure plate 650 causes the second energy-absorbing block 670 to compress and deform first. Since there is a clearance gap 690 between the bottom end of the first push rod 620 and the upper surface of the mounting block 680, the first pressure plate 630 connected to the first push rod 620 is not pushed by the air cushion 500. At this time, only the second energy-absorbing block 670 plays a buffering role. When the external impact load is large, the first energy-absorbing block 660 and the second energy-absorbing block 670 are compressed and deformed together to absorb energy. That is, the air cushion 500 pushes the second push rod 640, and the second pressure plate 650 causes the second energy-absorbing block 670 to compress and deform first. Then, the second push rod 640 continues to move to eliminate the clearance gap 690, and the bottom end of the first push rod 620 abuts against the upper surface of the mounting block 680. The first push rod 620 drives the first pressure plate 630, causing the first energy-absorbing block 660 to compress and deform to achieve secondary buffering.

[0036] If the energy-absorbing blocks have a single stiffness, they cannot adapt to impacts of varying intensities. Therefore, in one embodiment, both the first energy-absorbing block 660 and the second energy-absorbing block 670 are metal honeycomb structures, designed to deform under pressure to absorb impact energy. The stiffness of the first energy-absorbing block 660 is greater than that of the second energy-absorbing block 670. Metal honeycomb structures possess stable compressive energy absorption characteristics, are lightweight, and have high energy absorption efficiency. Specifically, the first energy-absorbing block 660 is a metal honeycomb structure with relatively high stiffness, large compressive deformation energy, and high array density. The second energy-absorbing block 670 is a metal honeycomb structure with relatively low stiffness, small compressive deformation energy, and low array density. Through this graded energy absorption design, matched buffering performance can be provided under different impact intensities, preventing excessive stiffness under small impacts from causing the impact force to be directly transmitted to the body, and insufficient buffering under large impacts from causing the energy-absorbing blocks to collapse prematurely.

[0037] The preferred embodiments of the present invention have been described in detail above, but the present invention is not limited to the embodiments described. Those skilled in the art can make various equivalent modifications or substitutions without departing from the spirit of the present invention, and these equivalent modifications or substitutions are all included within the scope defined by the claims of this application.

Claims

1. An emergency air cushion soft landing device for unmanned aerial vehicles, characterized in that, The device includes a frame, a triggering mechanism, a locking mechanism, an inflation mechanism, and an air cushion. The inflation mechanism includes a high-pressure gas cylinder, an energy storage device, a puncturing device, and an ejector pressurizing device. The high-pressure gas cylinder is mounted on the frame, and its opening is equipped with a sealing diaphragm. The puncturing device is slidably mounted on the frame towards the opening of the high-pressure gas cylinder to puncture the sealing diaphragm. The puncturing device has a gas channel connecting its two ends. The energy storage device is mounted on the frame, and its two ends abut against the frame and the puncturing device, respectively. The energy storage device has a tendency to move the puncturing device towards the opening of the high-pressure gas cylinder. The locking mechanism is mounted on the frame and is releaseable. The device is secured to the puncture component to restrict its movement. The triggering mechanism is mounted on the frame and signal-connected to the locking mechanism to control the locking mechanism to release the puncture component. The ejector pressurizing component includes a cavity and a one-way valve. The cavity is located at the end of the puncture component away from the high-pressure gas cylinder. The cavity contains a mixing chamber. The cavity also has an inlet that is sealed and connected to the outlet of the gas channel, an outlet that is connected to the air cushion, and at least one suction port that connects the mixing chamber to the external environment. The one-way valve is located at the suction port to prevent the gas in the mixing chamber from flowing back to the external environment. The air cushion is located at the bottom of the frame.

2. The emergency air cushion soft landing device for unmanned aerial vehicles according to claim 1, characterized in that, The puncture component's outlet extends into the mixing chamber, and the gas channel's outlet faces the gas port. A gap is left between the outer peripheral wall of the puncture component's outlet and the inner wall of the mixing chamber, and the gap is connected to the air intake. The outer diameter of the outer peripheral wall of the puncture component's outlet gradually decreases along the airflow direction.

3. The emergency air cushion soft landing device for unmanned aerial vehicles according to claim 1, characterized in that, The cross-sectional area of ​​the gas channel gradually decreases along the airflow direction.

4. The emergency air cushion soft landing device for unmanned aerial vehicles according to claim 1, characterized in that, The air inlet is threadedly sealed to the outer wall of the puncture component, and the air outlet is provided with an outwardly extending connecting part. The air cushion is connected to the connecting part through a flexible pipe.

5. The emergency air cushion soft landing device for unmanned aerial vehicles according to claim 1, characterized in that, The one-way valve includes a valve stem, an elastic element, and a sealing disc disposed at one end of the valve stem. The valve stem is slidably disposed on the cavity along the axial direction of the air intake. The sealing disc is located inside the mixing cavity. The elastic element is sleeved on the valve stem. The two ends of the elastic element abut against the cavity and the sealing disc, respectively. The elastic element has a tendency to move the sealing disc toward the air intake.

6. The emergency air cushion soft landing device for unmanned aerial vehicles according to claim 1, characterized in that, The triggering mechanism includes a housing, an air collection tube, a pressure-sensitive diaphragm, and a micro switch. The housing is located at the bottom of the frame. The pressure-sensitive diaphragm is sealed on the inner wall of the housing, dividing the interior of the housing into a pressure-sensitive chamber and an installation chamber. The housing has a vent hole corresponding to the pressure-sensitive chamber. The air collection tube is located at the bottom of the frame, with its input end facing downwards to catch the oncoming airflow when the drone crashes. The output end of the air collection tube is sealed and connected to the vent hole. The micro switch is located in the installation chamber, with its trigger end opposite to the pressure-sensitive diaphragm, so that the pressure-sensitive diaphragm deforms and presses the trigger end when the air pressure in the pressure-sensitive chamber reaches a set value. The micro switch is electrically connected to the locking mechanism.

7. The emergency air cushion soft landing device for unmanned aerial vehicles according to claim 6, characterized in that, The inlet of the gas collecting pipe is shaped like an inverted funnel, and the diameter of the inlet of the gas collecting pipe gradually increases from top to bottom.

8. The emergency air cushion soft landing device for unmanned aerial vehicles according to claim 1, characterized in that, The locking mechanism includes a driving device and a locking push rod. The locking push rod is slidably mounted on the frame. The sliding direction of the locking push rod intersects with the sliding direction of the puncturing member. One end of the locking push rod is provided with a fastening part. The outer wall of the puncturing member is provided with a groove that matches the fastening part. The driving device is mounted on the frame and is electrically connected to the triggering mechanism. The driving device is used to drive the locking push rod to slide so that the fastening part disengages from the groove.

9. The emergency air cushion soft landing device for unmanned aerial vehicles according to claim 1, characterized in that, It also includes a buffer assembly. The air cushion is disposed at the bottom of the frame via the buffer assembly. The buffer assembly includes a cylinder, a first push rod, a first pressure plate, a second push rod, a second pressure plate, a first energy-absorbing block, and a second energy-absorbing block. The cylinder is disposed at the bottom of the frame and is a hollow cylindrical structure with a downward opening. The first pressure plate is slidably disposed within the cylinder. The first energy-absorbing block abuts against the inner top wall of the cylinder and the upper surface of the first pressure plate. The first push rod is vertically disposed on the lower surface of the first pressure plate. The second pressure plate is slidably disposed within the cylinder and located at the first pressure plate. Below, the second energy-absorbing block is sleeved on the outside of the first push rod and abuts against the lower surface of the first pressure plate and the upper surface of the second pressure plate. The second push rod is fixed vertically to the lower surface of the second pressure plate. The second push rod is a hollow tubular structure. The first push rod is coaxial and slidably inserted inside the second push rod. A mounting block is provided at the end of the second push rod away from the second pressure plate. The air cushion is disposed on the lower surface of the mounting block. The bottom end of the first push rod and the upper surface of the mounting block are spaced apart to form a clearance gap. The height of the clearance gap is greater than or equal to the maximum compression thickness of the second energy-absorbing block.

10. The emergency air cushion soft landing device for unmanned aerial vehicles according to claim 9, characterized in that, Both the first and second energy-absorbing blocks are metal honeycomb structures used to deform under pressure to absorb impact energy. The stiffness of the first energy-absorbing block is greater than that of the second energy-absorbing block.

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