Automatic parachute separating device

Abstract

The invention provides an automatic parachute separating device, and relates to the technical field of parachutes, the automatic parachute separating device comprises a parachute cord pull rod, a barrel, a first limiting block, a first elastic body, a second elastic body, an action block and a second limiting block, a working cavity is formed in the barrel, the parachute cord pull rod comprises a first end and a second end, and a first annular recess is formed in the first end; the first limiting block is arranged in the first annular recess, the working cavity comprises a first cavity body, a second cavity body and a third cavity body, one end of the first elastic body is installed in the second cavity body, and the other end of the first elastic body abuts against the second limiting block; a second annular recess, a mounting through hole and a containing cavity are formed in the second end, the action block is mounted in the mounting through hole, the containing cavity is communicated with the mounting through hole, one end of the second elastic body is mounted in the containing cavity, and the other end of the second elastic body abuts against the action block; the second limiting block is installed in the second annular recess and abuts against the action block. External energy can be omitted, reliability is improved, air mistaken separation is prevented, and automatic separation is achieved.

Description

Technical Field

[0001] This invention relates to the field of parachute technology, and more specifically to an automatic parachute separation device. Background Technology

[0002] Currently, parachute separation devices are widely used in drones, aircraft recovery, and other fields to achieve reliable separation of parachutes from aircraft. Traditional separation devices mostly employ mechanical locking structures, relying on manual or electrical signals to trigger separation, which suffers from problems such as complex structures, response delays, or dependence on external energy. For example, some devices use electromagnetic locks or explosive bolts for separation, which, while highly reliable, are costly and have limited usage. Other purely mechanical structures may be falsely triggered during parachute deployment due to elastic rebound or vibration, resulting in premature separation or separation failure.

[0003] Furthermore, existing devices often fail to automatically trigger separation after landing, requiring manual intervention or specific terrain conditions, which limits their application in unattended or complex environments. Therefore, there is an urgent need for an automatic parachute separation device that is simple in structure, responds quickly, requires no external power source, and can reliably trigger separation. Summary of the Invention

[0004] In order to solve the technical problems in related technologies, the present invention provides an automatic parachute separation device that can achieve the effects of simple structure, rapid response, no need for external power and reliable triggering of separation.

[0005] To achieve the above objectives, the technical solution adopted by the present invention is as follows: This invention provides an automatic parachute separation device, including a parachute cord rod, a cylinder, a first limiting block, a first elastic body, a second elastic body, an actuating block, and a second limiting block. A through-hole working cavity is formed within the cylinder. The parachute cord rod passes through the working cavity and includes a first end and a second end disposed opposite to each other. The first end is used to connect to the parachute, and the end of the cylinder away from the first end is used to connect to an aircraft. A first annular recess is formed at the first end. The first limiting block is detachably disposed within the first annular recess and is used to abut against the end face of the cylinder near the first end. The working cavity includes a first cavity, a second cavity, and a third cavity sequentially distributed and connected along a direction from the first end to the second end. The radial dimension of the third cavity is larger than the radial dimension of the second cavity, and the radial dimension of the second cavity is larger than the radial dimension of the first cavity. One end of the first elastic body is installed in the second cavity, and the other end of the first elastic body extends into the third cavity and abuts against the second limiting block. The second end has a second annular recess and a mounting through hole extending radially along the paracord rod on its peripheral wall. The end face of the second end has an inward recess forming a receiving cavity extending axially along the paracord rod. In the direction connecting the first end and the second end, the height of the receiving cavity is greater than the height of the second annular recess. The actuating block is movably installed in the mounting through hole. The receiving cavity communicates with the mounting through hole. One end of the second elastic body is installed in the receiving cavity and the other end abuts against the actuating block. The second limiting block is detachably installed in the second annular recess and abuts against the bottom of the actuating block.

[0006] Optionally, both the first limiting block and the second limiting block are formed in pairs. The two first limiting blocks together form a ring structure to match the shape of the first annular recess, and the two second limiting blocks together form a ring structure to match the shape of the second annular recess.

[0007] Optionally, in the direction from the second end to the first end, the radial dimension of the first annular recess gradually increases; the first limiting block includes a first part and a second part connected to each other, the shape of the first part matches the shape of the first annular recess, and the second part is formed as a plate-like structure and is used to abut against the end face of the cylinder near the first end.

[0008] Optionally, in the direction from the first end to the second end, the radial dimension of the second annular recess gradually increases, the inner wall shape of the second limiting block is adapted to the outer wall shape of the second annular recess, and the two side surfaces of the actuating block are formed as wedge-shaped surfaces, which are adapted to the inner wall of the second limiting block, so that when the actuating block moves down, it can push the two second limiting blocks to separate from each other.

[0009] Optionally, the second elastic body is formed as a spring and installed in the receiving cavity; the automatic parachute separation device further includes a guide rod, the guide rod including a rod body portion and a limiting portion connected to each other, one end of the rod body portion away from the limiting portion is installed in the receiving cavity and passes through the second elastic body, the outer wall of the end of the rod body portion near the limiting portion is threadedly connected to the inner wall of the receiving cavity, the radial dimension of the limiting portion is larger than the radial dimension of the receiving cavity, and the limiting portion is used to abut against the second end.

[0010] Optionally, the first elastic body is configured as a spring, and in the direction from the first cavity to the third cavity, the projection of the first elastic body falls within the projection of the second cavity.

[0011] Optionally, the automatic parachute separation device further includes a damping baffle and two dampers. The damping baffle is sleeved on the first end, and the radial dimension of the damping baffle is larger than the radial dimension of the cylinder. The two dampers are installed opposite each other on both sides of the cylinder, and the damping baffle is configured to contact the dampers.

[0012] Optionally, the automatic parachute separation device further includes a U-shaped plate, the two ends of which are installed on both sides of the cylinder and correspond to the two dampers respectively, and the U-shaped plate is used to connect with the aircraft.

[0013] Beneficial effects: 1. Through the above technical solution, firstly, the present invention can achieve fully mechanical automatic separation without external energy dependence. Specifically, the automatic parachute separation device of the present invention is composed of purely mechanical components (e.g., parachute line rods, cylinder, etc.), and its energy source is the tension input transmitted by the parachute lines during the parachute opening process. This not only eliminates the need for external energy (completely eliminating dependence on external energy sources or complex control systems such as batteries, electrical control circuits, electromagnets, or explosive bolts), but also has high reliability (avoiding separation failures due to circuit faults, signal interference, power depletion, etc., making it particularly suitable for single-use, long-term standby, or harsh environmental scenarios). In addition, it has low cost and no limit on the number of uses (the core components are mechanical structures, which are inexpensive and effectively avoid the drawbacks of disposable components such as explosive bolts).

[0014] Secondly, this invention provides a dual-stage locking (first-stage locking and second-stage locking) and unlocking mechanism, which effectively prevents accidental separation in mid-air. Specifically, in the initial stage (before parachute opening), the first-stage locking is achieved by the first limiting block being engaged in the first annular recess of the parachute cord pull rod and abutting against the end face of the tube, as well as the elastic force of the first elastic body, mainly bearing the initial load before parachute opening; the second-stage locking is achieved by the second limiting block abutting against the step surface, mainly bearing the continuous pull of the parachute after opening and before landing. Thus, at the moment of parachute opening, the first-stage locking is first unlocked (the first limiting block is pulled out), and the device enters a "pre-unlocked" state, but the second-stage locking quickly takes over, relocking the device. This process absorbs the impact of parachute opening and can prevent the single locking mechanism from failing instantly due to the impact. At the same time, during descent, as long as the parachute provides a continuous upward pull, the second limiting block will be tightly engaged on the step surface, and the second locking mechanism will not have the problem of accidental locking. Thus, it can effectively solve the problem of "false triggering caused by elastic rebound or vibration in purely mechanical structures".

[0015] Third, this invention utilizes the mechanical changes during landing as a trigger signal to achieve automatic triggering. Specifically, the working logic of this invention is entirely based on force changes. The locking state in the second stage relies on the upward tension continuously borne by the parachute cord rod and the interlocking force between the step surface, the second limiting block, and the parachute cord rod to achieve dynamic balance. Specifically, in the air state, the second limiting block is tightly pressed against the step surface, and the device is locked. After landing, the tension disappears, the force balance is broken, and the downward elastic force of the first and second elastic bodies becomes the dominant force, pushing the parachute cord rod and the second limiting block downward, creating conditions for unlocking. In this way, it is equivalent to creating a mechanical "force sensor" that can automatically sense the air state and the landing state and automatically achieve separation, effectively overcoming the shortcomings of existing related technologies that "require manual intervention or specific terrain conditions".

[0016] Fourth, the invention features a highly integrated structure and ingenious operational logic. Specifically, all functional components operate within the working cavity of the cylindrical body. Through a stepped cavity design (first cavity, second cavity, and third cavity), a natural track for the movement of the limiting block and a locking step surface are formed. The up-and-down movement of the parachute cord linkage connects the actions of all components. Thus, all functions are completed within a single cylindrical mechanism, resulting in a small overall size, light weight, and compact structure, facilitating installation on aircraft. Furthermore, the series of actions—the upward movement of the linkage, the compression of the first elastic body, the formation of the second locking mechanism, the downward movement of the linkage, and the disengagement of the second limiting block—are interconnected, logically clear, and highly reliable. This "one-stick driven" design simplifies the structure and reduces the number of parts.

[0017] Overall, this invention, through a purely mechanical double-locking mechanism and a triggering mechanism based on mechanical balance, successfully produces a series of positive technical effects: it not only eliminates the need for external energy but also greatly improves reliability. Furthermore, it effectively prevents accidental separation in mid-air and enables automatic separation after landing.

[0018] 2. Other beneficial effects or advantages of the present invention will be described in detail in the specific embodiments. 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 description of 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] in: Figure 1 This is a three-dimensional structural diagram of an automatic parachute separation device provided in an exemplary embodiment of the present invention; Figure 2 This is an exploded structural diagram of an automatic parachute separation device provided in an exemplary embodiment of the present invention; Figure 3 yes Figure 2 Enlarged schematic diagram of the local structure at point A; Figure 4 This is a cross-sectional schematic diagram of a cylindrical body provided in an exemplary embodiment of the present invention; Figures 5 to 9 This is a schematic diagram of the separation process of an automatic parachute separation device provided in an exemplary embodiment of the present invention, wherein... Figure 5 This is a schematic diagram of the initial locked state of the automatic parachute separation device. Figure 6 This is a diagram showing the first limiting block disengaging during the initial stage of parachute deployment. Figure 7 This is a diagram illustrating the buffer phase during parachute deployment. Figure 8 This is a schematic diagram showing the second limiting block displacing out of the cylinder during the umbrella opening process. Figure 9 This is a schematic diagram of the second limit block disengaging during the umbrella opening process.

[0021] Explanation of the labels in the attached drawings: 100-Automatic parachute separation device; 1-Parachute line pull rod; 11-First end; 111-First annular recess; 12-Second end; 121-Second annular recess; 122-Mounting through hole; 123-Receiving cavity; 2-Cylinder; 21-Working cavity; 211-First cavity; 212-Second cavity; 213-Third cavity; 3-First limiting block; 31-First part; 32-Second part; 41-First elastic body; 42-Second elastic body; 5-Actuating block; 51-Wedge-shaped surface; 6-Second limiting block; 7-Guide rod; 71-Rod part; 72-Limiting part; 81-Damping baffle; 82-Damper; 9-U-shaped plate. Detailed Implementation

[0022] The technical solution of the present invention will be described in detail below with reference to the accompanying drawings.

[0023] like Figures 1 to 9As shown, the present invention provides an automatic parachute separation device 100, including a parachute cord pull rod 1, a cylindrical body 2, a first limiting block 3, a first elastic body 41, a second elastic body 42, an actuating block 5, and a second limiting block 6. A through-hole working cavity 21 is formed inside the cylindrical body 2, and the parachute cord pull rod 1 passes through the working cavity 21. The parachute cord pull rod 1 includes a first end 11 and a second end 12 disposed opposite to each other. The first end 11 is used to connect with the parachute, and the end of the cylindrical body 2 away from the first end 11 is used to connect with the aircraft. A first annular recess 111 is formed on the first end 11. The first limiting block 3 is detachably disposed on the first annular recess 111. The first limiting block 3 is used to abut against the end face of the cylinder 2 near the first end 11. The working cavity 21 includes a first cavity 211, a second cavity 212 and a third cavity 213 that are sequentially distributed and connected along the direction from the first end 11 to the second end 12. The radial dimension of the third cavity 213 is larger than the radial dimension of the second cavity 212. The radial dimension of the second cavity 212 is larger than the radial dimension of the first cavity 211. One end of the first elastic body 41 is installed in the second cavity 212, and the other end of the first elastic body 41 extends into the third cavity 213 and abuts against the second limiting block 6. The second end 12 has a second annular recess 121 and a mounting through hole 122 that extends radially along the paracord rod 1. The end face of the second end 12 has an inward recess forming a receiving cavity 123 that extends axially along the paracord rod 1. In the direction of the line connecting the first end 11 and the second end 12, the height of the receiving cavity 123 is greater than the height of the second annular recess 121. The actuating block 5 is movably installed in the mounting through hole 122. The receiving cavity 123 communicates with the mounting through hole 122. One end of the second elastic body 42 is installed in the receiving cavity 123 and the other end abuts against the actuating block 5. The second limiting block 6 is separably installed in the second annular recess 121 and abuts against the bottom of the actuating block 5.

[0024] To facilitate a clear and accurate understanding of the present invention by those skilled in the art, the working process / working principle of the automatic parachute separation device 100 of the present invention will be described below in conjunction with the accompanying drawings.

[0025] In the initial state, that is, when the parachute is not deployed (see [reference]). Figure 5 As shown), at this time, the parachute lines are connected to the parachute line lever 1, and the canopy 2 is connected to the aircraft. During the initial parachute deployment phase (as shown...), Figure 6As shown, the parachute pulls the parachute line lever 1 upwards. At this time, the first end 11 will bring the first limiting block 3 out of the working cavity 21 of the cylinder 2, so that the first limiting block 3 loses its limit and automatically disengages, causing the automatic parachute separation device 100 to unlock. At the same time, the second end 12 of the parachute line lever 1 drives the second limiting block 6 upwards and compresses the first elastic body 41 until the second limiting block 6 is stuck on the step surface between the second cavity 212 and the third cavity 213, and the parachute line lever 1 will stop moving upwards. In the air, the parachute line lever 1 is continuously subjected to an upward force (continuously subjected to the tension of the parachute lines), so that the automatic parachute separation device 100 is in working condition.

[0026] Once the entire automatic parachute separation device has landed, it enters the landing state (see reference). Figure 8 and Figure 9 (As shown). After landing, the parachute line lever 1 is no longer under the tension of the parachute lines. At this time, the first elastic body 41 will push the second limiting block 6 and the parachute line lever 1 downwards. The second limiting block 6 will be removed from the cylinder 2 after a certain period of time (as shown). Figure 8 (As shown). Afterwards, the second elastic body 42 will continue to push the action block 5 downward, and the action block 5 will cause the second limiting block 6 to move outward so that it disengages.

[0027] In addition, if the wind blows the parachute, the parachute rope lever 1 will be automatically pulled out of the tube 2, achieving automatic separation.

[0028] In other words, the automatic parachute separation device 100 of the present invention includes three states: an initial state, an aerial state, and a landing state. In the initial state, as... Figure 5 As shown, at this time, the first elastic body 41 is in a state of applying elastic force to the outside, that is, it applies a downward thrust to the second limiting block 6. However, since the second limiting block 6 is blocked by the second end 12, and the first limiting block 3 is located in the first annular recess 111 and abuts against the end face of the cylinder 2, the entire device will remain stable. In the air, as... Figure 6 and Figure 7 As shown, first, please refer to Figure 6 When the parachute first opens, the parachute line lever 1 is forcibly pulled upwards by the parachute, causing the first limiting block 3 to move upwards to the outside of the cylinder 2 and then detach, thus unlocking the entire device. Simultaneously, the upward movement of the parachute line lever 1 compresses the first elastic body 41 until the second limiting block 6, driven by the second end 12, abuts against the end face where the second cavity 212 and the third cavity 213 meet, at which point the device reaches a stable state in the air, i.e., as... Figure 7 As shown, at this time, the entire device is in working condition, ensuring that the parachute will not separate from the tube 2 (thus preventing the parachute from separating from the aircraft). During landing, as... Figure 8As shown, after the parachute lands, it will no longer exert tension on the parachute line lever 1. The first elastic body 41 will push the second limiting block 6 downward, causing the parachute line lever 1 to move downward. Thus, the second limiting block 6 will be pushed out of the cylinder 2 after a certain period of time. Afterward, the second elastic body 42 will continue to push the action block 5 downward, as... Figure 9 As shown, at this time, the action block 5 will push the second limit block 6 to disengage, thereby completing the unlocking of the parachute rope lever 1 and the cylinder 2, that is, completing the unlocking of the parachute and the aircraft.

[0029] Through the above technical solution, firstly, the present invention can achieve fully mechanical, automatic separation without external energy dependence. Specifically, the automatic parachute separation device 100 of the present invention is composed of purely mechanical components (e.g., parachute line lever 1, cylinder 2, etc.). Its energy source is the tension input transmitted by the parachute lines during the parachute opening process. This not only eliminates the need for external energy (completely freeing it from dependence on external energy sources or complex control systems such as batteries, electrical control circuits, electromagnets, or explosive bolts), but also has high reliability (avoiding separation failures due to circuit faults, signal interference, power depletion, etc., making it particularly suitable for single-use, long-term standby, or harsh environmental scenarios). In addition, it has low cost and no limit on the number of uses (the core components are mechanical structures, which are inexpensive and effectively avoid the drawbacks of disposable components such as explosive bolts).

[0030] Secondly, this invention provides a two-stage locking (first-stage locking and second-stage locking) and unlocking mechanism, which can effectively prevent accidental separation in mid-air. Specifically, in the initial stage (before the parachute opens), the first-stage locking is achieved by the first limiting block 3 being engaged in the first annular recess 111 of the parachute line lever 1 and abutting against the end face of the tube 2, as well as the elastic force of the first elastic body 41, mainly bearing the initial load before the parachute opens; the second-stage locking is achieved by the second limiting block 6 abutting against the step surface, mainly bearing the continuous pull of the parachute after opening and before landing. Thus, at the moment of parachute opening, the first-stage locking is first unlocked (the first limiting block 3 is pulled out), and the device enters a "pre-unlocked" state, but the second-stage locking quickly takes over, locking the device again. This process absorbs the impact of parachute opening and can prevent the single locking mechanism from failing instantly due to the impact. At the same time, during the descent, as long as the parachute provides a continuous upward pull, the second limiting block 6 will be tightly engaged on the step surface, and the second locking mechanism will not have the problem of accidental locking. This effectively solves the problem of "false triggering caused by elastic rebound or vibration in purely mechanical structures".

[0031] Third, this invention utilizes the mechanical changes during landing as a trigger signal to achieve automatic triggering. Specifically, the working logic of this invention is entirely based on force changes. The locking state in the second stage relies on the upward tension continuously borne by the parachute cord lever 1 and the interlocking force between the step surface, the second limiting block 6, and the parachute cord lever 1 to achieve dynamic balance. In the air state, the second limiting block 6 is tightly pressed against the step surface, and the device is locked. After landing, the tension disappears, the force balance is broken, and the downward elastic force of the first elastic body 41 and the second elastic body 42 becomes the dominant force, pushing the parachute cord lever 1 and the second limiting block 6 downward respectively, creating conditions for unlocking. In this way, it is equivalent to creating a mechanical "force sensor" that can automatically sense the air state and the landing state and automatically achieve separation, effectively overcoming the shortcomings of existing related technologies that "require manual intervention or specific terrain conditions".

[0032] Fourth, the invention features a highly integrated structure and ingenious operational logic. Specifically, all functional components are integrated within the working cavity 21 of the cylindrical body 2. Through the stepped cavity design (first cavity 211, second cavity 212, and third cavity 213), a track for the movement of the limiting block and a locking step surface are naturally formed. The up-and-down movement of the parachute cord lever 1 connects the actions of all components. In this way, all functions are completed within a single cylindrical mechanism, resulting in a small overall size, light weight, and compact structure, making it easy to install and arrange on aircraft. Moreover, the series of actions, such as the upward movement of the lever, the compression of the first elastic body 41, the formation of the second locking mechanism, the downward movement of the lever, and the disengagement of the second limiting block 6, are interconnected, logically clear, and highly reliable. This "one-lever driven" design simplifies the structure and reduces the number of parts.

[0033] Overall, this invention, through a purely mechanical double-locking mechanism and a triggering mechanism based on mechanical balance, successfully produces a series of positive technical effects: it not only eliminates the need for external energy but also greatly improves reliability. Furthermore, it effectively prevents accidental separation in mid-air and enables automatic separation after landing.

[0034] In one embodiment of the present invention, such as Figure 2 , Figures 5 to 9 As shown, the first limiting block 3 and the second limiting block 6 of the present invention are both formed in two. The two first limiting blocks 3 together form an annular structure to match the shape of the first annular recess 111, and the two second limiting blocks 6 together form an annular structure to match the shape of the second annular recess 121.

[0035] In this way, by setting the first limiting block 3 and the second limiting block 6 as two separate blocks forming a ring, the locking force can be applied symmetrically and evenly to the first end 11 (first annular recess 111) and the second end 12 (second annular recess 121). This symmetrical layout avoids the eccentric force or stress concentration that may occur from a single block, ensuring the stability of the locking state and reducing the risk of accidental loosening due to uneven force.

[0036] Secondly, the first limiting block 3 and the second limiting block 6 are designed as two blocks that provide the necessary conditions for radial movement. When unlocking is required, the two separate blocks can synchronously and smoothly separate radially to both sides, thereby disengaging from the corresponding annular recesses and completing the unlocking action. This design also facilitates reassembly of the two blocks from the outside to the inside during reset, making the operation simpler.

[0037] Third, compared to machining a complete sleeve-shaped part with an inner conical surface, manufacturing two relatively simple block parts is easier to achieve in terms of process and lower in cost. Furthermore, during assembly, the two blocks can be combined and placed into the corresponding cavities or recesses, which can also effectively reduce the assembly difficulty.

[0038] In one embodiment of the present invention, such as Figure 2 As shown, in the direction from the second end 12 to the first end 11, the radial dimension of the first annular recess 111 gradually increases; the first limiting block 3 includes a first part 31 and a second part 32 connected to each other. The shape of the first part 31 matches the shape of the first annular recess 111, and the second part 32 is formed as a plate structure and is used to abut against the end face of the cylinder 2 near the first end 11.

[0039] Thus, by configuring the first annular recess 111 and the corresponding first limiting block 3 as described above, firstly, reliable self-locking and smooth unlocking can be achieved. The first annular recess 111 is designed with a structure whose radial dimension gradually increases (i.e., conical or V-shaped), and matches with the first part 31 of the first limiting block 3 to form a sloping self-locking mechanism. In this way, when locking, when the paracord lever 1 is subjected to an upward pulling force, the sloping structure will effectively convert the axial pulling force into a force that forces the first limiting block 3 to press radially, making the locking more secure and preventing it from loosening during vibration. At the same time, when unlocking, only a relatively small force is needed to move the first limiting block 3 radially outward slightly to break the self-locking state. Then the paracord lever 1 can easily move upward, allowing the first part 31 to slide out of the recess, achieving smooth and effortless unlocking.

[0040] Secondly, the second part 32 is set as a plate structure and abuts against the end face of the cylinder 2. This not only effectively increases the bearing area and disperses the pressure, preventing damage or deformation of the end face of the cylinder 2 or the limiting block under high pressure, thus improving the durability and reliability of the device, but also clearly defines the final position of the first limiting block 3 in the locked state, effectively preventing it from being over-embedded or having an uncertain position, and ensuring the stability of the axial limiting effect.

[0041] In one embodiment of the present invention, such as Figure 3 As shown, in the direction from the first end 11 to the second end 12, the radial dimension of the second annular recess 121 gradually increases, the inner wall shape of the second limiting block 6 is adapted to the outer wall shape of the second annular recess 121, and the two side surfaces of the actuating block 5 are formed as wedge-shaped surfaces 51. The wedge-shaped surfaces 51 are adapted to the inner wall of the second limiting block 6 so that when the actuating block 5 moves down, it can push the two second limiting blocks 6 to separate from each other.

[0042] Thus, through the configuration of the second annular recess 121 and the actuating block 5, firstly, a sloped self-locking mechanism, identical to that of the first locking stage (see the sloped self-locking principle of the first annular recess 111 above), can be achieved. When the parachute opens, the tension of the parachute lines is transmitted through the line lever 1, forcing the actuating block 5 to move the second limiting block 6 upwards, abutting against the stepped surface. At this time, the upward force acts on the slope of the second limiting block 6, pressing it radially inwards and making it more firmly locked within the second annular recess 121. This design ensures the stability of the second-stage locking under continuous upward tension, greatly enhancing the locking reliability of the device from parachute opening to landing.

[0043] Secondly, it ensures smooth and reliable unlocking of the second limiting block 6 after landing. Specifically, upon landing, the tension exerted by the parachute lines on the parachute line lever 1 disappears, and it is no longer axially compressed. At this time, the downward force exerted by the second elastic body 42 on the actuating block 5 is converted into a force that pushes the two second limiting blocks 6 radially outward through the matching wedge surface 51, causing them to smoothly disengage from the second annular recess 121, thus completing the final unlocking. This design, which utilizes a mechanical inclined plane to automatically convert axial movement into radial movement, ensures the automaticity and reliability of the separation action without any external intervention.

[0044] In one embodiment of the present invention, such as Figure 2 , Figures 5 to 9As shown, the second elastic body 42 of the present invention can be formed as a spring and installed in the receiving cavity 123; the automatic parachute separation device 100 also includes a guide rod 7, which includes a rod body portion 71 and a limiting portion 72 connected to each other. The end of the rod body portion 71 away from the limiting portion 72 is installed in the receiving cavity 123 and passes through the second elastic body 42. The outer wall of the end of the rod body portion 71 near the limiting portion 72 is threadedly connected to the inner wall of the receiving cavity 123. The radial dimension of the limiting portion 72 is larger than the radial dimension of the receiving cavity 123, and the limiting portion 72 is used to abut against the second end 12.

[0045] In this way, firstly, the formed receiving cavity 123 can provide installation space for the second elastic body 42. This is an embedded design that can effectively avoid adding extra structural length or volume to the outside of the cylinder 2 to accommodate the spring, greatly optimizing the utilization of internal space and making the axial structure of the entire device more compact and small.

[0046] Secondly, the guide rod 7 passes through the receiving cavity 123 and the second elastic body 42, forming a precision guiding mechanism. This mechanism ensures that the elastic force generated by the second elastic body 42 is strictly transmitted axially during compression and release, preventing the spring from bending, being unbalanced, or jamming, and ensuring the accuracy and consistency of the force direction, thereby making the movement of the action block 5 more reliable and smooth.

[0047] Third, the threaded rod portion 71 also facilitates the installation, replacement, and maintenance of the guide rod 7 and the second elastic body 42.

[0048] In one embodiment of the present invention, such as Figures 5 to 9 As shown, the first elastic body 41 of the present invention can be configured as a spring, and in the direction from the first cavity 211 to the third cavity 213, the projection of the first elastic body 41 falls within the projection of the second cavity 212.

[0049] Thus, firstly, by specifically defining the first elastic body 41 as a spring, its properties as a reliable and linearly effective elastic element are clearly defined. This ensures that it provides predictable and consistent elastic force during compression and release, which is the basis for the device to achieve the timed triggering function. At the same time, the condition that "the projection falls within the projection of the second cavity 212" means that the radial dimension of the spring is limited by the inner wall of the corresponding second cavity 212, which can play a guiding role to effectively prevent the spring from bending, becoming unstable, or getting stuck during compression, ensuring that its force is always transmitted axially, thereby ensuring the accurate and reliable movement trajectory of the second limiting block 6 and the paracord pull rod 1 assembly.

[0050] Secondly, it ensures that the first elastic body 41 will not experience radial friction or collision with the stepped surface or other structures of the third cavity 213 throughout the entire movement. This precise spatial planning avoids additional resistance, wear, or functional failure caused by unnecessary contact between parts, making the movement of the internal moving parts of the device smoother and more efficient.

[0051] In one embodiment of the present invention, such as Figure 1 , Figure 2 , Figures 5 to 9 As shown, the automatic parachute separation device 100 of the present invention may further include a damping baffle 81 and two dampers 82. The damping baffle 81 is sleeved on the first end 11, and the radial dimension of the damping baffle 81 is larger than the radial dimension of the cylinder 2. The two dampers 82 are installed opposite to each other on both sides of the cylinder 2. The damping baffle 81 is configured to be able to contact the dampers 82.

[0052] In this embodiment, while in the air (e.g.) Figure 7 As shown), at the moment the parachute lines are straightened, due to the elasticity of the lines, the parachute line lever 1 will briefly stop bearing the upward force. At this time, the first elastic body 41 will push the second limiting block 6 and the parachute line lever 1 to move downward. The damping baffle 81 will contact the damper 82, and the damper 82 will slow down the downward speed of the parachute line lever 1 to prevent the second limiting block 6 from coming off in the air.

[0053] Thus, firstly, during the parachute opening process, the parachute lines may experience a momentary decrease in tension due to elasticity after straightening. At this time, the first elastic body 41 will push the parachute line lever 1 assembly downwards. The damping baffle 81 will contact the damper 82 as the lever moves downwards. The damper 82 will significantly slow down the downward movement of the parachute line lever 1 by providing resistance (such as friction, hydraulic damping, etc.). This delay ensures that the downward stroke is insufficient to disengage the second limit block 6 from the step surface. Subsequently, the continuous parachute line tension will pull the lever back up, and the device will return to the locked state. This effectively avoids premature separation caused by tension fluctuations in the air.

[0054] Second, this design incorporates an "intelligent" delay mechanism: the resistance of the damper 82 is less than the final elastic force of the first elastic body 41. In the air, the brief downward movement is suppressed by the damper 82. Upon landing, the parachute tension disappears, and the first elastic body 41 propels the component to continue its downward movement. Although the initial velocity is slowed by the damper 82, the sustained elastic force eventually overcomes the damping force, ensuring that the second limit block 6 has sufficient time and force to complete the final disengagement action, thus guaranteeing that the separation function will ultimately be triggered.

[0055] In one embodiment of the present invention, such as Figure 1 , Figure 2 and Figure 7As shown, the automatic parachute separation device 100 of the present invention may further include a U-shaped plate 9, the two ends of which are installed on both sides of the cylinder 2 and correspond to two dampers 82 respectively. The U-shaped plate 9 is used to connect with the aircraft.

[0056] In this way, firstly, the cylinder 2 can focus on its core function (accommodating the locking and disengagement mechanism) without needing to design complex mounting points on its body, simplifying the structure and manufacturing of the cylinder 2. At the same time, the U-shaped plate 9 can be specially designed according to the specific location and form of the mounting point on the aircraft, providing greater installation flexibility and adaptability.

[0057] Secondly, the two ends of the U-shaped plate 9 are installed on both sides of the cylinder 2 and correspond to the damper 82. This is equivalent to adding a robust "reinforcing beam" or "mounting bridge" at the location where the damper 82 is installed. When the damper 82 is working (especially when it is impacted by the damping baffle 81), the U-shaped plate 9 can effectively disperse and absorb these local loads, preventing them from being entirely borne by the wall of the cylinder 2. This enhances the stiffness and strength of the mounting point of the damper 82, reduces the risk of deformation or damage under vibration or impact, and ensures the long-term reliability of the damping function.

[0058] The above are merely specific embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. An automatic parachute separation device, characterized in that, The system includes a parachute cord rod (1), a cylindrical body (2), a first limiting block (3), a first elastic body (41), a second elastic body (42), an actuating block (5), and a second limiting block (6). A through-hole working cavity (21) is formed within the cylindrical body (2). The parachute cord rod (1) passes through the working cavity (21). The parachute cord rod (1) includes a first end (11) and a second end (12) arranged opposite to each other. The first end (11) is used to connect with a parachute. The end of the cylindrical body (2) away from the first end (11) is used to connect with an aircraft. A first annular recess (111) is formed in the first end (111). The first limiting block (3) is detachably disposed within the first annular recess (111). The first limiting block (3) is used to abut against the end face of the cylinder (2) near the first end (11). The working cavity (21) includes a first cavity (211), a second cavity (212) and a third cavity (213) that are sequentially distributed and connected along the direction from the first end (11) to the second end (12). The radial dimension of the third cavity (213) is greater than the radial dimension of the second cavity (212). The radial dimension of the second cavity (212) is greater than the radial dimension of the first cavity (211). One end of the first elastic body (41) is installed in the second cavity (212), and the other end of the first elastic body (41) extends into the third cavity (213) and abuts against the second limiting block (6). The second end (12) has a second annular recess (121) and a mounting through hole (122) that extends through the paracord rod (1) in the radial direction on its peripheral wall. The end face of the second end (12) has an inward recess forming a receiving cavity (123) that extends axially along the paracord rod (1). In the direction of the line connecting the first end (11) and the second end (12), the height of the receiving cavity (123) is greater than the height of the second annular recess (121). The actuating block (5) is movably installed in the mounting through hole (122). The receiving cavity (123) communicates with the mounting through hole (122). One end of the second elastic body (42) is installed in the receiving cavity (123) and the other end abuts against the actuating block (5). The second limiting block (6) is detachably installed in the second annular recess (121) and abuts against the bottom of the actuating block (5).

2. The automatic parachute separation device according to claim 1, characterized in that, The first limiting block (3) and the second limiting block (6) are both formed in two. The two first limiting blocks (3) together form a ring structure to match the shape of the first annular recess (111). The two second limiting blocks (6) together form a ring structure to match the shape of the second annular recess (121).

3. The automatic parachute separation device according to claim 2, characterized in that, In the direction from the second end (12) to the first end (11), the radial dimension of the first annular recess (111) gradually increases; the first limiting block (3) includes a first part (31) and a second part (32) connected to each other, the shape of the first part (31) matches the shape of the first annular recess (111), and the second part (32) is formed as a plate structure and is used to abut against the end face of the cylinder (2) near the first end (11).

4. The automatic parachute separation device according to claim 2, characterized in that, In the direction from the first end (11) to the second end (12), the radial dimension of the second annular recess (121) gradually increases, the inner wall shape of the second limiting block (6) is adapted to the outer wall shape of the second annular recess (121), and the two side surfaces of the action block (5) are formed as wedge-shaped surfaces (51). The wedge-shaped surfaces (51) are adapted to the inner wall of the second limiting block (6) so that when the action block (5) moves down, it can push the two second limiting blocks (6) to separate from each other.

5. The automatic parachute separation device according to claim 4, characterized in that, The second elastic body (42) is formed as a spring and installed in the receiving cavity (123); the automatic parachute separation device also includes a guide rod (7), the guide rod (7) includes a rod body portion (71) and a limiting portion (72) connected to each other, the end of the rod body portion (71) away from the limiting portion (72) is installed in the receiving cavity (123) and passes through the second elastic body (42), the outer wall of the end of the rod body portion (71) near the limiting portion (72) is threaded to the inner wall of the receiving cavity (123), the radial dimension of the limiting portion (72) is greater than the radial dimension of the receiving cavity (123), and the limiting portion (72) is used to abut against the second end (12).

6. The automatic parachute separation device according to claim 1, characterized in that, The first elastic body (41) is configured as a spring, and in the direction from the first cavity (211) to the third cavity (213), the projection of the first elastic body (41) falls within the projection of the second cavity (212).

7. The automatic parachute separation device according to claim 1, characterized in that, The automatic parachute separation device further includes a damping baffle (81) and two dampers (82). The damping baffle (81) is sleeved on the first end (11), and the radial dimension of the damping baffle (81) is larger than the radial dimension of the cylinder (2). The two dampers (82) are installed opposite to each other on both sides of the cylinder (2). The damping baffle (81) is configured to be able to contact the dampers (82).

8. The automatic parachute separation device according to claim 7, characterized in that, The automatic parachute separation device also includes a U-shaped plate (9), the two ends of which are installed on both sides of the cylinder (2) and correspond to the two dampers (82) respectively. The U-shaped plate (9) is used to connect with the aircraft.

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