Rapid parachute ejection device for emergency rescue of unmanned aerial vehicle

Abstract

The invention relates to a rapid parachute ejection device for emergency rescue of an unmanned aerial vehicle. The rapid parachute ejection device comprises a main shell, an upper end cover, a parachute and an ejection system. The ejection system is arranged at the bottom in the main shell, and the parachute is folded and surrounded between the ejection system and the main shell; and the upper end cover is buckled at the top of the main shell and is bounced off after the ejection system is started. The parachute rope of the parachute of the rapid parachute ejection device is connected to the unmanned aerial vehicle through the main shell, the top of the parachute is connected to the upper end cover, no redundant objects fall to the ground after the device works, and damage to the ground is reduced. The multi-stage catapult cylinders are arranged in a stacked and sleeved mode, the height of the catapult system can be effectively reduced, the storage space of the parachute is increased, and the catapult device can be developed towards the miniaturization and flattening direction.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicles, in particular to a rapid ejection parachute device for emergency rescue of unmanned aerial vehicles. BACKGROUND

[0002] The ejection parachute device is generally installed on the unmanned aerial vehicle for emergency use when the unmanned aerial vehicle encounters an accident. The unmanned aerial vehicle has high requirements for the weight and volume of such additional safety devices, so the future development trend of the ejection parachute device is towards miniaturization and flattening.

[0003] The existing ejection parachute device generally has two types of parachute compartments and ejection structures, one of which is separated, connected by a piston in the middle, and the other is in the same chamber. The disadvantage of the former ejection parachute device is that the structure is complex, the total height of the device is high, and in addition, the piston structure may fly out with the parachute, which has the risk of injuring people after landing. The disadvantage of the latter ejection parachute device is that the ejection device occupies a large space in the parachute compartment, resulting in a large total height, which is not conducive to the development of the ejection parachute device towards miniaturization and flattening. For example, the existing patent application CN118811094A discloses a technical solution of an ejection parachute device and an unmanned aerial vehicle, which adopts a piston slidingly connected to the cavity wall of the accommodating cavity, and separates the accommodating cavity into an inflation cavity and a parachute cavity. The parachute cavity is connected to the ejection opening. The air inlet of the seat body can be inflated and pressurized by high-temperature gas to drive the piston together with the parachute bag to slide towards the ejection opening. The piston and the parachute bag fly out of the ejection opening together, and the parachute bag opens under the action of the airflow to assist the unmanned aerial vehicle to land. This belongs to the state of separation of the parachute compartment and the ejection structure. In addition, the existing patent application CN220764694U discloses an unmanned aerial vehicle parachute ejection propulsion system, which is composed of a top cover, a gas collecting assembly, an energy storage assembly, a parachute compartment main body and a wire harness assembly. This structure is simple and belongs to an integrated structure, but the ejection mechanism occupies a large space in the parachute compartment, which is not conducive to the miniaturization of the device. SUMMARY

[0004] The technical problem to be solved by the present application is to provide a rapid ejection parachute device for emergency rescue of unmanned aerial vehicles to solve the above problems.

[0005] The present application is achieved by the following technical solutions:

[0006] A kind of quick ejection parachute device for emergency rescue of unmanned aerial vehicle, the quick ejection parachute device includes main shell, upper end cover, parachute and ejection system;The ejection system is set in the bottom of the main shell, the parachute is folded around between the ejection system and the main shell, the parachute rope is connected to unmanned aerial vehicle by the main shell, the top of the parachute is connected to the upper end cover;The upper end cover is buckled on the top of the main shell, and is ejected after the ejection system starts.

[0007] Further, the quick ejection parachute device for emergency rescue of unmanned aerial vehicle, the ejection system includes multi-stage ejection cylinder and gas power source arranged in the multi-stage ejection cylinder;The multi-stage ejection cylinder includes outer ejection cylinder connected to the bottom of the main shell and inner ejection cylinder slidable along the outer ejection cylinder;Under the action of the gas power source, the inner ejection cylinder slides upward along the outer ejection cylinder to eject the upper end cover.

[0008] Further, the quick ejection parachute device for emergency rescue of unmanned aerial vehicle, the multi-stage ejection cylinder further includes at least one intermediate ejection cylinder slidingly arranged between the outer ejection cylinder and the inner ejection cylinder;Under the action of the gas power source, the intermediate ejection cylinder and the inner ejection cylinder slide upward along the outer ejection cylinder to eject and unfold to eject the upper end cover.

[0009] Further, the quick ejection parachute device for emergency rescue of unmanned aerial vehicle, the outer ejection cylinder is open upward and downward, the lower port extends outward to form a connecting part, and the upper port extends inward to form a first limiting step;The intermediate ejection cylinder is sleeved in the outer ejection cylinder, and the upper and lower openings of the intermediate ejection cylinder extend outward to form a first positioning protrusion matched with the first limiting step, and the upper port extends inward to form a second limiting step;The inner ejection cylinder is sleeved in the intermediate ejection cylinder, and the lower end opening and the upper end are sealed, and the lower port extends outward to form a second positioning protrusion matched with the second limiting step.

[0010] Further, the quick ejection parachute device for emergency rescue of unmanned aerial vehicle, sliding seals are arranged between the outer ejection cylinder and the intermediate ejection cylinder, and between the intermediate ejection cylinder and the inner ejection cylinder.

[0011] Further, the quick ejection parachute device for emergency rescue of unmanned aerial vehicle, the height of the multi-stage ejection cylinder in the ejection and unfolding state is greater than the height of the main shell.

[0012] Further, the quick ejection parachute device for emergency rescue of the unmanned aerial vehicle, the gas production power source comprises an ignition base, an electric igniter, an electric igniter fixing ring, a medicine box and a gas production agent; the electric igniter fixing ring is arranged in the ignition base from the top of the ignition base, the gas production agent is arranged in the medicine box, and the medicine box is arranged at the top of the ignition base.

[0013] Further, the quick ejection parachute device for emergency rescue of the unmanned aerial vehicle, the main shell, the outer ejection barrel and the ignition base are fixedly connected together.

[0014] Further, the quick ejection parachute device for emergency rescue of the unmanned aerial vehicle, the outer circle of the canopy of the parachute is provided with an air bag and an inflation device, and the exhaust port pull rope of the inflation device is connected with the bottom of the main shell.

[0015] Further, the quick ejection parachute device for emergency rescue of the unmanned aerial vehicle, the outer circle of the canopy of the parachute is provided with an air bag, and the air bag is provided with a memory alloy.

[0016] The advantages and effects of the present application are as follows:

[0017] 1. The quick ejection parachute device provided by the present application comprises an ejection system, the ejection system comprises a multi-stage ejection barrel and a gas production power source arranged in the multi-stage ejection barrel, and the parachute is folded and surrounded between the ejection system and the main shell, so that the high-temperature gas is isolated from the parachute, and the parachute can be prevented from being burned.

[0018] 2. The multi-stage ejection barrel of the quick ejection parachute device is arranged in a telescopic mode, so that the height of the ejection system can be effectively reduced, the storage space of the parachute is increased, and the development of the ejection device in the direction of miniaturization and flattening is facilitated.

[0019] 3. The parachute rope of the quick ejection parachute device is connected to the unmanned aerial vehicle through the main shell, and the top of the parachute is connected to the upper end cover, so that no redundant object falls to the ground after the device is operated, and the damage to the ground is reduced.

[0020] 4. The quick ejection parachute device provided by the present application can be reused except that the ejection system cannot be reused, so that the use cost is reduced.

[0021] 5. Compared with other parachute devices, the quick ejection parachute device provided by the present application can further shorten the opening time of the parachute, so that the use requirement of the parachute in an emergency is met. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1Fig. 1 is a structural schematic diagram of a quick ejection parachute device according to the present application in a non-working state;

[0023] Figure 2 Fig. 2 is a structural schematic diagram of an ejection system of a quick ejection parachute device according to the present application;

[0024] Figure 3 Fig. 3 is a structural schematic diagram of a quick ejection parachute device according to the present application in a working state;

[0025] Figure 4 Fig. 4 is a structural schematic diagram of a parachute of an embodiment of a quick ejection parachute device according to the present application;

[0026] Figure 5 Fig. 5 is a structural schematic diagram of a parachute of another embodiment of a quick ejection parachute device according to the present application.

[0027] Fig. 1 is a structural schematic diagram of a quick ejection parachute device according to the present application in a non-working state; DETAILED DESCRIPTION

[0028] In order to make the purposes, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings. The described embodiments are part of the embodiments of the present application, rather than all the embodiments of the present application. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to explain the present application, and cannot be understood as a limitation of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application. The embodiments of the present application will be described in detail below with reference to the accompanying drawings:

[0029] In the description of the present application, it is to be understood that, unless otherwise specified, the meaning of "a plurality of" is two or more; the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is merely intended to facilitate the description of the present application and simplify the description, and is not intended to indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the scope of protection of the present application. In addition, the terms "first", "second", etc. are used only for descriptive purposes and cannot be understood as indicating or implying relative importance. In the description of the present application, it is also to be noted that, unless otherwise specified and limited, the terms "mounting", "connecting", "connection" should be understood broadly, for example, it can be fixed connection, or detachable connection, or integral connection; it can be direct connection, or indirect connection through intermediate medium. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0030] Figure 1 The structure schematic diagram of the quick ejection parachute device provided by the present application in the non-working state is shown. The quick ejection parachute device comprises a main shell 2, an upper end cover 1, a parachute 3 and an ejection system 4. The main shell 2 has a cavity inside, the ejection system 4 is arranged at the bottom of the main shell 2, so that the longitudinal section of the cavity inside the main shell 2 forms a concave shape. The parachute 3 is folded and wrapped in the concave cavity between the ejection system 4 and the main shell 2. The upper end cover 1 is buckled on the top of the main shell 2 and is bounced away after the ejection system 4 is started. Specifically, the main shell 2 and the upper end cover 1 adopt clearance fit, and are fixed through a shear pin 6. The shear pin 6 is pulled off after the ejection system 4 works, so as to drive the separation action between the main shell 2 and the upper end cover 1. The parachute cord of the parachute 3 is connected to the unmanned aerial vehicle through the main shell 2, and the top of the parachute 3 is connected to the upper end cover 1. Specifically, a circular ring screw 5 is connected to the unmanned aerial vehicle through the bottom of the main shell 2, and the parachute cord of the parachute cord is connected to the circular ring screw 5.

[0031] The main function of the shear pin 6 is to provide initial energy accumulation for the upper end cover 1. 10ms-20ms before the ejection system 4 acts, the ejection cylinder hits the upper end cover 1 upward, at this time the impact force has not reached the shear force of the shear pin 6, the shear pin 6 is not cut off, and is in the energy accumulation stage. After reaching a certain shear force later, the shear pin 6 is cut off, and the upper end cover 1 is immediately ejected.

[0032] The circular screw 5 has two functions. One is to connect the quick ejection parachute device to the unmanned aerial vehicle body through the circular screw 5. The other is to connect the top of the circular screw 5 to the bottom of the parachute rope of the parachute 3, so that the parachute rope of the parachute 3 is connected to the unmanned aerial vehicle through the main shell 2. In this way, after the parachute 3 is ejected and straightened, a pulling force can be quickly generated on the unmanned aerial vehicle.

[0033] Figure 2 A structure diagram of an ejection system of the quick ejection parachute device provided by the application is shown. The ejection system comprises a multi-stage ejection cylinder and a gas power source arranged in the multi-stage ejection cylinder. In one embodiment, the multi-stage ejection cylinder comprises an outer ejection cylinder 48 connected to the bottom of the main shell 2 and an inner ejection cylinder 46 which can slide along the outer ejection cylinder 48. Under the action of the gas power source, the inner ejection cylinder 46 slides upward along the outer ejection cylinder 48 to pop open the upper end cover 1.

[0034] As Figure 2 shown, in another embodiment, the multi-stage ejection cylinder further comprises at least one intermediate ejection cylinder 47 which is arranged between the outer ejection cylinder 48 and the inner ejection cylinder 46. Under the action of the gas power source, the intermediate ejection cylinder 47 and the inner ejection cylinder 46 slide upward along the outer ejection cylinder 48 to pop open the upper end cover 1.

[0035] The outer ejection cylinder 48 is open at the top and the bottom, the lower end thereof extends outward to form a connecting portion for connecting and fixing the bottom of the main shell 2, and the upper end thereof extends inward to form a first limiting step. The intermediate ejection cylinder 47 is sleeved in the outer ejection cylinder 48 and is open at the top and the bottom, the lower end thereof extends outward to form a first positioning protrusion matched with the first limiting step, so as to avoid the intermediate ejection cylinder 47 from being separated from the outer ejection cylinder 48 when the intermediate ejection cylinder 47 slides upward, and the upper end thereof extends inward to form a second limiting step. The inner ejection cylinder 46 is sleeved in the intermediate ejection cylinder 47 and is open at the lower end and sealed at the upper end, and an internal cavity is formed in the inner ejection cylinder 46, in which the gas power source is arranged. The lower end of the inner ejection cylinder 46 extends outward to form a second positioning protrusion matched with the second limiting step, so as to avoid the inner ejection cylinder 46 from being separated from the intermediate ejection cylinder 47 when the inner ejection cylinder 46 slides upward. The intermediate ejection cylinder 47 can also have multiple ejection cylinders, so that the volume of the ejection system is compressed smaller or the overall ejection distance is farther. Figure 3 As shown, the limit position of the upward sliding of the inner ejection cylinder 46 is at the intersection of the top end of the second positioning protrusion of the inner ejection cylinder 46 and the bottom end of the second limiting step of the intermediate ejection cylinder 47. The limit position of the upward sliding of the intermediate ejection cylinder 47 is at the intersection of the top end of the first positioning protrusion of the intermediate ejection cylinder 47 and the bottom end of the first limiting step of the outer ejection cylinder 48. The height of the ejection and unfolding state of the multi-stage ejection cylinder, i.e. the limit positions of the sliding of the inner ejection cylinder 46, the intermediate ejection cylinder 47 and the outer ejection cylinder 48 after superposition, is greater than the height of the main shell 2, so that it can be ensured that the upper end cover 1 is ejected out along the preset route.

[0036] The outer ejection tube 48, the intermediate ejection tube 47, and the inner ejection tube 46 are of the same height and their dimensions are mutually compatible, forming a sealing structure between them in both the non-operating and operating states. Sliding seals are provided between the outer ejection tube 48 and the intermediate ejection tube 47, and between the intermediate ejection tube 47 and the inner ejection tube 46. Specifically, at least one annular groove for a sealing ring is formed on the outer side of the positioning protrusion of each ejection tube (in this embodiment, the intermediate ejection tube 47 and the inner ejection tube 46). Adjacent ejection tubes are fitted with a clearance fit, allowing them to slide freely relative to each other. The sealing ring is fitted into the annular groove and abuts against the inner wall of the adjacent ejection tube, providing a gas seal between the adjacent ejection tubes.

[0037] The gas-generating power source includes an ignition base 41, an electric igniter 42, an electric igniter retaining ring 43, a cartridge 44, and a gas-generating agent 45. The electric igniter retaining ring 43 presses the electric igniter 42 from the top of the ignition base 41 into the ignition base 41. The gas-generating agent 45 is installed inside the cartridge 44, which is inverted and mounted on the top of the ignition base 41. The electric igniter retaining ring 43 is interference-fitted with the ignition base 41. The ignition base 41 secures the cartridge 44 by means of a flange. In one embodiment, the bottom of the ignition base 41 has a flange extending outward along the outer wall of the bottom of the main housing 2 through the bottom of the main housing 2. During installation, the gas power source is inserted into the bottom of the main housing 2 from bottom to top outside the bottom of the main housing 2. The flange of the ignition base 41 is engaged with the bottom of the main housing 2. Several threaded holes are provided at the corresponding positions of the connecting part of the outer ejection tube 48, the bottom of the main housing 2, and the flange of the ignition base 41. The ignition base 41, the main housing 2, and the outer ejection tube 48 are fixedly connected together by screws, and the sealing rings between them form a closed cavity for the entire ejection system.

[0038] like Figure 4 As shown, in one embodiment, the outer ring of the parachute 3's canopy 31 is provided with an airbag 32 and at least one inflation device 33. The inflation device 33 is filled with liquid butane, and the exhaust cable of the inflation device 33 is connected to the bottom of the main shell 2. After the ejection system is activated, the upper cover 1 is ejected, the parachute is launched, the cable is broken, the liquid butane rapidly vaporizes, inflating the airbag 32 and quickly opening the bottom circular surface of the parachute 3, allowing the parachute to fully deploy.

[0039] like Figure 5 As shown, in another embodiment, an airbag 32 is provided around the outer edge of the canopy 31 of the parachute 3, and a shape memory alloy 34 is disposed inside the airbag 32. When the rapid ejection parachute device is not in operation, the shape memory alloy 34 is folded and stored together with the parachute 3 inside the main shell 2. Once the parachute 3 is ejected from the main shell, the shape memory alloy 34 immediately returns to its original shape, quickly opening the bottom circular surface of the parachute 3, allowing the parachute to fully deploy.

[0040] The ejection parachute device is fixed with the unmanned aerial vehicle body through a ring screw. When the electric igniter in the ejection system receives a failure signal, the electric igniter works to ignite the gas generating agent in the medicine box. The gas generating agent is completely combusted in 30 ms, and the high-temperature and high-pressure gas generated enters the multi-stage ejection cylinder to push the inner ejection cylinder 46, the intermediate ejection cylinder 47 and the outer ejection cylinder 48 to move upward in turn. Since the total height of the multi-stage ejection cylinder at the limit position is greater than the height of the main shell 2, when the accumulated energy exceeds the shearing force of the shearing pin 6, the shearing pin is pulled off, and the upper end cover is ejected. The top of the parachute 3 connected with the upper end cover is also ejected out of the main shell. At the moment when the parachute 3 is ejected out of the main shell 2, the canopy of the parachute is accelerated to be unfolded. The parachute cord at the bottom of the parachute 3 is connected with the ring screw, and after the parachute cord is straightened, the parachute is fully opened under the action of the airflow to assist the unmanned aerial vehicle to land.

[0041] The above examples are only used to illustrate the technical solutions of the present application, and are not used to limit the implementation scope of the present application. Any equivalent changes and modifications made within the protection scope of the present application shall be considered to fall within the protection scope of the present application.

Claims

1. A rapid ejection parachute device for emergency rescue using unmanned aerial vehicles, characterized in that, The rapid ejection parachute device includes a main shell (2), an upper cover (1), a parachute (3), and an ejection system (4); the ejection system (4) is located at the bottom inside the main shell (2), the parachute (3) is folded and surrounds the ejection system (4) and the main shell (2), the parachute lines of the parachute (3) are connected to the drone through the main shell (2), and the top of the parachute (3) is connected to the upper cover (1); the upper cover (1) is fastened to the top of the main shell (2) and is ejected after the ejection system (4) is activated.

2. The rapid ejection parachute device for emergency rescue using unmanned aerial vehicles according to claim 1, characterized in that, The ejection system includes a multi-stage ejection tube and a gas-generating power source disposed within the multi-stage ejection tube; the multi-stage ejection tube includes an outer ejection tube (48) connected to the bottom of the main housing (2) and an inner ejection tube (46) that can slide along the outer ejection tube (48); under the action of the gas-generating power source, the inner ejection tube (46) slides upward along the outer ejection tube (48) to eject the upper end cover (1).

3. A rapid ejection parachute device for emergency rescue using unmanned aerial vehicles according to claim 2, characterized in that, The multi-stage ejection tube also includes at least one intermediate ejection tube (47) slidably disposed between the outer ejection tube (48) and the inner ejection tube (46); under the action of the gas-generating power source, the intermediate ejection tube (47) and the inner ejection tube (46) slide upward along the outer ejection tube (48) and eject and unfold to open the upper end cover (1).

4. A rapid ejection parachute device for emergency rescue using unmanned aerial vehicles according to claim 3, characterized in that, The outer ejector tube (48) has openings at the top and bottom, with its lower port extending outward to form a connecting part and its upper port extending inward to form a first limiting step; the middle ejector tube (47) is fitted inside the outer ejector tube (48), with openings at the top and bottom, with its lower port extending outward to form a first positioning protrusion that cooperates with the first limiting step, and its upper port extending inward to form a second limiting step; the inner ejector tube (46) is fitted inside the middle ejector tube (47), with an opening at the lower end and a sealed upper end, and its lower port extending outward to form a second positioning protrusion that cooperates with the second limiting step.

5. A rapid ejection parachute device for emergency rescue using unmanned aerial vehicles according to claim 4, characterized in that, A sliding seal is provided between the outer ejection tube (48) and the intermediate ejection tube (47), and between the intermediate ejection tube (47) and the inner ejection tube (46).

6. A rapid ejection parachute device for emergency rescue of unmanned aerial vehicles according to any one of claims 2 to 5, characterized in that, The height of the multi-stage catapult in its deployed state is greater than the height of the main shell (2).

7. A rapid ejection parachute device for emergency rescue using unmanned aerial vehicles according to claim 2, characterized in that, The gas-generating power source includes an ignition base (41), an electric igniter (42), an electric igniter fixing ring (43), a medicine box (44), and a gas-generating agent (45); the electric igniter fixing ring (43) presses the electric igniter (42) from the top of the ignition base (41) into the ignition base (41), the gas-generating agent (45) is installed in the medicine box (44), and the medicine box (44) is located at the top of the ignition base (41).

8. A rapid ejection parachute device for emergency rescue using unmanned aerial vehicles according to claim 7, characterized in that, The main housing (2), the outer ejection tube (48), and the ignition base (41) are fixedly connected together.

9. A rapid ejection parachute device for emergency rescue using unmanned aerial vehicles according to claim 2, characterized in that, The parachute (3) has an airbag (32) and an inflation device (33) on the outer ring of the canopy (31). The exhaust port rope of the inflation device (33) is connected to the bottom of the main shell (2).

10. A rapid ejection parachute device for emergency rescue using unmanned aerial vehicles according to claim 2, characterized in that, The parachute (3) has an airbag (32) on the outer ring of its canopy (31), and a shape memory alloy (34) is disposed inside the airbag (32).

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