Modular unmanned aerial vehicle emergency parachute deployment device

Abstract

This invention belongs to the field of emergency parachute landing and protection technology for unmanned aerial vehicles (UAVs). It provides a modular UAV emergency parachute landing device, including an ejection tube fixedly connected to the UAV body. A parachute is placed inside the ejection tube and fixedly connected to it. An opening is provided at the end of the ejection tube furthest from the UAV body, and a detachable cover is connected to the opening. An ejection assembly includes a push-out component disposed within the ejection tube, and a gas generator assembly is also disposed within the ejection tube. The gas generator assembly provides the power source for the push-out component to eject the parachute from the ejection tube. This invention adopts a modular design and a non-pyrotechnic, room-temperature gas ejection structure, solving the problems of existing devices such as easy scorching of the parachute, susceptibility to moisture, and inconvenient maintenance. It achieves the goals of safety and reliability, simple interface, quick installation, and low operating cost, and is suitable for the emergency parachute landing needs of various low-altitude aircraft.

Description

Technical Field

[0001] This invention belongs to the field of emergency safety parachute landing and protection technology for unmanned aerial vehicles (UAVs), and particularly relates to a modular UAV emergency parachute landing device. Background Technology

[0002] With the deepening implementation of my country's national strategy for developing a low-altitude economy, related technologies in this field have developed rapidly. Various types of unmanned aerial vehicles (UAVs) and electric vertical takeoff and landing (EVTOL) aircraft have been widely used in scenarios such as logistics distribution, agricultural plant protection, emergency rescue, and urban air traffic. At the same time, the safety issues of these aircraft have become increasingly prominent, especially the frequent crashes caused by power system failures, structural failures, and flight control anomalies, which pose a real threat to the lives and property of the people.

[0003] Currently, existing drone parachute systems on the market mainly fall into two categories: one is the traditional ejection-type parachute system that relies on pyrotechnics such as gunpowder or nitrocellulose as a power source; the other is a passive system that releases the parachute electrically or mechanically. The former has significant safety hazards, such as the high temperature of the gunpowder gas, which can easily burn the parachute canopy, leading to parachute failure; at the same time, pyrotechnics are prone to moisture absorption and deterioration during long-term storage. Although the latter avoids the use of pyrotechnics, its response speed is slow, its ejection force is limited, and it is difficult to reliably open the parachute at high speeds or in complex postures, thus limiting its applicable scenarios.

[0004] Furthermore, existing parachute systems are mostly non-modular in design, with complex interfaces, often requiring customized modifications for different aircraft models, resulting in long installation cycles and high costs. At the same time, many systems lack effective sealing designs, making the parachutes susceptible to moisture, mold, and corrosion during long-term use, leading to frequent and costly maintenance. These problems severely restrict the widespread application of parachute systems in low-altitude aircraft. Summary of the Invention

[0005] The purpose of this invention is to provide a modular emergency parachute landing device for unmanned aerial vehicles (UAVs) to solve the problems of existing parachute landing devices being prone to scorching the parachute, being susceptible to moisture, and being inconvenient to maintain, thereby achieving the goal of safety, reliability, modularity, and rapid installation.

[0006] To achieve the above objectives, the present invention provides the following solution: a modular unmanned aerial vehicle (UAV) emergency parachute landing device, comprising: The ejection tube is fixedly connected to the body of the UAV. A parachute is placed inside the ejection tube and fixedly connected to the ejection tube. An opening is provided at the end of the ejection tube away from the body, and a tube cover is detachably connected to the opening. The ejection assembly includes a pusher disposed within the ejection tube, and a gas generator assembly is also disposed within the ejection tube, the gas generator assembly being used to provide a power source for the pusher to eject the parachute from the ejection tube.

[0007] Preferably, the ejector includes a piston plate slidably connected inside the ejection tube, the side of the piston plate near the opening being fixedly connected to the parachute belts, and the gas generator assembly being used to push the piston plate toward the opening.

[0008] Preferably, the gas generator assembly includes a gas cylinder, which is fixedly connected inside the ejection tube and located on the side of the piston plate away from the opening. The gas cylinder's outlet is connected to a housing, and the housing has an air hole. The housing has an opening for piercing the outlet, and the outlet is connected to the air hole through a gas channel provided inside the housing.

[0009] Preferably, the opening component includes a piston pin slidably connected within the gas channel and an ignition head disposed on the housing. The ignition head is used to push the piston pin toward the gas outlet of the gas cylinder, and the piston pin is used to puncture the gas outlet of the gas cylinder.

[0010] Preferably, a plurality of parachute lifting points are fixedly connected to the inner side of the ejection tube and the end away from the opening, and the piston plate is fixedly connected to the plurality of parachute lifting points by a sling.

[0011] Preferably, the side wall of the cylinder cover is provided with multiple insertion holes, and the side wall of the ejector tube near the opening is provided with multiple through holes. The multiple through holes are correspondingly arranged with the multiple insertion holes, and a shearing pin is inserted between the through holes and the insertion holes.

[0012] Preferably, a sealing ring is fixedly sleeved on the side wall of the cylinder cover, and when the cylinder cover is connected to the opening, the sealing ring abuts against the inner wall of the ejection cylinder.

[0013] Preferably, the ejection tube, tube cover, piston plate, and parachute lifting point are made of composite materials.

[0014] Preferably, the gas cylinder stores high-pressure, room-temperature gas.

[0015] Preferably, the parachute is one of a flat round parachute, a square parachute, or a cross parachute.

[0016] Compared with the prior art, the present invention has the following advantages and technical effects: 1. The emergency parachute device of the present invention adopts a modular and internal force transmission design, which can be easily and conveniently connected with various low-altitude aircraft on the market, and can be quickly installed without customized modification.

[0017] 2. This invention replaces existing gunpowder generators or nitrocellulose and other hazardous materials with a gas generator assembly. It is not subject to hazardous materials control restrictions, is easy to use, and has high reliability. At the same time, no high-temperature gas is generated, so it will not burn the parachute, thus improving system safety. It also prevents the agent from getting damp, has high operational reliability, and reduces maintenance requirements.

[0018] 3. The parachute of the present invention can be packaged in the ejection tube with a high packaging density. The tube cover can prevent the parachute from getting wet or deteriorating due to moisture, thus reducing maintenance requirements. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. 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.

[0020] Figure 1 This is a cross-sectional view of the emergency parachute device of the present invention; Figure 2 This is a cross-sectional schematic diagram of the catapult tube of the present invention; Figure 3 This is a cross-sectional schematic diagram of the gas generator assembly of the present invention; Figure 4 This is a schematic diagram of the connection structure between the ejection tube and the tube cover of the present invention; The components are as follows: 1. Parachute; 2. Ejection tube; 21. Tube cover; 211. Shear pin; 212. Sealing ring; 22. Tube body; 23. Piston plate; 24. Parachute lifting point; 25. Base plate; 3. Gas generator assembly; 31. Gas cylinder; 32. Shell; 33. End cap; 34. Ignition head; 35. Piston firing pin; 4. Controller. Detailed Implementation

[0021] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0022] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0023] Reference Figures 1-4This invention provides a modular unmanned aerial vehicle (UAV) emergency parachute landing device, comprising: The ejection tube 2 is fixedly connected to the drone body. A parachute 1 is placed inside the ejection tube 2. The parachute 1 is fixedly connected to the ejection tube 2. An opening is provided at the end of the ejection tube 2 away from the drone body. A tube cover 21 is detachably connected to the opening. The ejection assembly includes an ejector disposed within the ejection tube 2. The ejection tube 2 also contains a gas generator assembly 3, which provides a power source for the ejector to eject the parachute 1 from the ejection tube 2.

[0024] The main function of the ejection tube 2 is to serve as an integral mounting base, fixedly connected to the UAV body, and to provide housing space for the parachute 1 and ejection assembly. The main function of the parachute 1 is to deploy after ejection, providing deceleration and emergency parachute landing capabilities for the UAV. The main function of the tube cover 21 is to seal the opening of the ejection tube 2 to prevent foreign objects from entering, and to be pushed out during ejection so that the parachute 1 can be ejected. The main function of the ejector is to push the parachute 1 out of the ejection tube 2 under the drive of the gas generator assembly 3. The main function of the gas generator assembly 3 is to provide the power source for the ejector to push the parachute 1 out of the ejection tube 2. Overall, this invention adopts a modular design, non-pyrotechnic room-temperature gas ejection, and a multi-sealing structure, solving the problems of easy scorching of the parachute, susceptibility to moisture, and inconvenient maintenance of existing devices. It achieves the goals of safety and reliability, simple interface, quick installation, and low operating cost, and is suitable for the emergency parachute landing needs of various low-altitude aircraft.

[0025] The scheme is further optimized, and the ejector component includes a piston plate 23, which is slidably connected inside the ejection tube 2. The side of the piston plate 23 near the opening is fixedly connected to the parachute belt of the parachute 1. The gas generator assembly 3 is used to push the piston plate 23 to move towards the opening.

[0026] In a further optimized design, the gas generator assembly 3 includes a gas cylinder 31, which is fixedly connected inside the ejection tube 2. The gas cylinder 31 is located on the side of the piston plate 23 away from the opening. The gas outlet of the gas cylinder 31 is connected to a housing 32. An air hole is provided on the housing 32. An opening for piercing the air outlet is provided inside the housing 32. The air outlet is connected to the air hole through a gas channel provided inside the housing 32.

[0027] The design is further optimized so that the opening component includes a piston pin 35 slidably connected in the gas channel and an ignition head 34 disposed on the housing 32. The ignition head 34 is used to push the piston pin 35 to move toward the gas outlet of the gas cylinder 31, and the piston pin 35 is used to puncture the gas outlet of the gas cylinder 31.

[0028] like Figure 1 and Figure 3As shown, the gas passage is a through hole opened in the housing 32, with one end connected to the gas outlet of the gas cylinder 31. A piston striker 35 and an ignition head 34 are then installed sequentially from the other end. Finally, an end cap 33 is used to fix the through hole to the end of the housing 32 away from the gas cylinder, thereby sealing the through hole. The vent and the through hole are connected on the side closest to the gas cylinder.

[0029] After receiving the ignition signal, the ignition head 34 generates gas, which pushes the piston pin 35 to move along the gas passage in the housing 32 toward the gas outlet of the gas cylinder 31. The piston pin 35 punctures the gas outlet, and the high-pressure room temperature gas stored in the gas cylinder 31 is released and discharged from the gas hole on the housing 32 through the gas passage. A high-pressure zone is generated between the piston plate 23 and the bottom of the ejection tube 2, which in turn pushes the piston plate 23 to launch the parachute 1 at a certain speed, thereby straightening and inflating the parachute.

[0030] Further optimization of the design includes a controller 4, which is electrically connected to the ignition head 34. The controller 4 integrates a MEMS inertial sensor, an accelerometer, a processor, and a power supply module, and encapsulates a flight runaway judgment algorithm program. It has the function of autonomously activating the parachute device, thereby autonomously igniting the ignition head 34.

[0031] With further optimization, the ignition head 34 can be directly connected to the UAV flight control system, and the flight control system can directly activate the ignition head 34.

[0032] In a further optimized design, multiple parachute sling points 24 are fixedly connected to the inner side of the ejection tube 2 and the end furthest from the opening. The piston plate 23 is fixedly connected to the multiple parachute sling points 24 via slings.

[0033] Further optimize the plan, such as Figure 2 As shown, the ejection tube 2 includes a tube body 22, and a base plate 25 is fixedly connected to the bottom of the tube body 22. The base plate 25 and the tube body 22 are sealed by a sealing ring. Mounting feet are provided on the base plate 25 or the tube body 22 to facilitate fixed connection with the UAV body.

[0034] In this embodiment, the piston plate 23 is connected to the parachute strap to the parachute 1 at the top and to the parachute suspension point 24 at the bottom, thereby transmitting the aerodynamic load of the parachute to the mounting feet and finally to the fuselage.

[0035] In a further optimized design, multiple insertion holes are provided on the side wall of the cylinder cover 21, and multiple through holes are provided on the side wall of the ejection tube 2 near the opening. The multiple through holes are corresponding to the multiple insertion holes, and shear pins 211 are inserted between the through holes and the insertion holes.

[0036] In this embodiment, when the piston plate 23 pushes the parachute 1, the parachute 1 pushes the tube cover 21, thereby cutting the shear pin between the tube cover 21 and the tube body 22, thus launching the parachute 1 at a certain speed. In a further optimized design, a sealing ring 212 is fixedly fitted on the side wall of the cylinder cover 21. When the cylinder cover 21 is connected to the opening, the sealing ring 212 abuts against the inner wall of the ejection tube 2.

[0037] like Figure 4 As shown, the sealing ring 212 can prevent rainwater and moisture from entering the ejection tube 2 and corroding the parachute 1, thereby improving maintainability.

[0038] Further optimization of the design resulted in the use of composite materials for the ejection tube 2, tube cover 21, piston plate 23, and parachute lifting point 24.

[0039] The design was further optimized so that high-pressure, room-temperature gas is stored in gas cylinder 31.

[0040] In this embodiment, the high-pressure, room-temperature, non-toxic, and pollution-free gas released by the gas cylinder 31 can avoid the problem of scorching the propellant parachute when using conventional gas generators or propellant parachutes such as nitrocellulose, as well as the problem of easy moisture damage and failure during long-term storage. Further optimization of the design: Parachute 1 adopts one of the following: a flat round parachute, a square parachute, or a cross parachute (including its improved versions), which has the characteristics of low manufacturing cost and good performance.

[0041] In the description of this invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0042] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Various modifications and improvements made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.

Claims

1. A modular unmanned aerial vehicle (UAV) emergency parachute landing device, characterized in that, include: The ejection tube (2) is fixedly connected to the body of the UAV. A parachute (1) is placed inside the ejection tube (2). The parachute (1) is fixedly connected to the ejection tube (2). An opening is provided at one end of the ejection tube (2) away from the body. A tube cover (21) is detachably connected inside the opening. The ejection assembly includes a pusher disposed within the ejection tube (2), and a gas generator assembly (3) is also disposed within the ejection tube (2), the gas generator assembly (3) being used to provide the pusher with a power source to eject the parachute (1) from the ejection tube (2).

2. The modular UAV emergency parachute device according to claim 1, characterized in that: The ejector includes a piston plate (23) which is slidably connected inside the ejection tube (2). The side of the piston plate (23) near the opening is fixedly connected to the parachute belt of the parachute (1). The gas generator assembly (3) is used to push the piston plate (23) to move towards the opening.

3. The modular UAV emergency parachute device according to claim 2, characterized in that: The gas generator assembly (3) includes a gas cylinder (31), which is fixedly connected inside the ejector tube (2) and is located on the side of the piston plate (23) away from the opening. The gas outlet of the gas cylinder (31) is connected to a housing (32), and the housing (32) has an air hole. The housing (32) is provided with an opening for piercing the air outlet. The air outlet is connected to the air hole through a gas channel provided inside the housing (32).

4. A modular UAV emergency parachute device according to claim 3, characterized in that: The opening component includes a piston pin (35) slidably connected in the gas channel and an ignition head (34) disposed on the housing (32). The ignition head (34) is used to push the piston pin (35) toward the gas outlet of the gas cylinder (31). The piston pin (35) is used to puncture the gas outlet of the gas cylinder (31).

5. A modular UAV emergency parachute device according to claim 2, characterized in that: Multiple parachute slings (24) are fixedly connected to the inner side of the ejection tube (2) and the end away from the opening. The piston plate (23) is fixedly connected to the multiple parachute slings (24) by a sling.

6. A modular UAV emergency parachute device according to claim 1, characterized in that: The cylinder cover (21) has multiple insertion holes on its side wall, and the ejector tube (2) has multiple through holes on its side wall near the opening. The multiple through holes are corresponding to the multiple insertion holes, and a shear pin (211) is inserted between the through holes and the insertion holes.

7. A modular UAV emergency parachute device according to claim 1, characterized in that: A sealing ring (212) is fixedly sleeved on the side wall of the cylinder cover (21). When the cylinder cover (21) is connected to the opening, the sealing ring (212) abuts against the inner wall of the ejection tube (2).

8. A modular UAV emergency parachute device according to claim 5, characterized in that: The ejection tube (2), tube cover (21), piston plate (23), and parachute suspension point (24) are made of composite materials.

9. A modular UAV emergency parachute device according to claim 3, characterized in that: The gas cylinder (31) stores high-pressure, room-temperature gas.

10. A modular UAV emergency parachute device according to claim 1, characterized in that: The parachute (1) is one of a flat round umbrella, a square umbrella, or a cross umbrella.

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