Automatic parachute release

Abstract

The application provides an automatic parachute separation device, and relates to the technical field of parachutes, which comprises a parachute rope pull rod, a cylinder, a first limiting block, a first elastic body, a second elastic body, a moving block and a second limiting block, a working cavity is formed in the cylinder, the parachute rope pull rod comprises a first end and a second end, the first end is provided with a first annular recess, the first limiting block is arranged in the first annular recess, the working cavity comprises a first cavity, a second cavity and a third cavity, one end of the first elastic body is installed in the second cavity, and the other end abuts against the second limiting block; the second end is provided with a second annular recess, a mounting through hole and a containing cavity, the moving block is installed in the mounting through hole, the containing cavity is in communication with the mounting through hole, one end of the second elastic body is installed in the containing cavity, and the other end abuts against the moving block; and the second limiting block is installed in the second annular recess and abuts against the moving block. The application can save external energy, improve reliability, prevent air separation and realize automatic separation.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of parachutes, in particular to an automatic parachute separation device. BACKGROUND

[0002] At present, parachute separation devices are widely used in the fields of unmanned aerial vehicles, aircraft recovery, etc., for realizing reliable separation of parachutes and aircrafts. Traditional separation devices mostly adopt mechanical locking structures, rely on manual or electrical signals to trigger separation, and have problems such as complex structure, delayed response or dependence on external energy. For example, some devices use electromagnetic locks or explosive bolts to achieve separation, which has high reliability but high cost and limited use times; some purely mechanical structures may be mis-triggered due to elastic rebound or vibration during parachute opening, causing premature separation or separation failure.

[0003] In addition, existing devices often cannot automatically trigger separation after landing, and need to rely on manual intervention or specific terrain conditions, limiting their application in unattended or complex environments. Therefore, there is an urgent need for a parachute automatic separation device with simple structure, rapid response, no external energy and reliable separation triggering. SUMMARY

[0004] In order to solve the technical problems in the related art, the present application provides a parachute automatic separation device, which can realize the effects of simple structure, rapid response, no external energy and reliable separation triggering.

[0005] In order to achieve the above purpose, the technical scheme adopted by the present application is as follows:

[0006] The present application provides a parachute automatic separation device, comprising a parachute rope pull rod, a barrel, a first limiting block, a first elastic body, a second elastic body, a moving block and a second limiting block. The barrel forms a through working cavity inside, the parachute rope pull rod is arranged in the working cavity, the parachute rope pull rod comprises a first end and a second end arranged oppositely, the first end is used for connecting with a parachute, one end of the barrel away from the first end is used for connecting with an aircraft, the first end forms a first annular recess, the first limiting block is arranged in the first annular recess in a detachable manner, and the first limiting block is used for abutting against an end face of the barrel close to the first end, the working cavity comprises a first cavity, a second cavity and a third cavity distributed and communicated in sequence along a direction from the first end to the second end, the radial dimension of the third cavity is greater than that of the second cavity, and the radial dimension of the second cavity is greater than that 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.

[0007] The second end is provided with a second annular recess and a mounting through hole penetrating along the radial direction of the umbrella rope pull rod, and the end face of the second end is recessed inward to form an accommodating cavity extending along the axial direction of the umbrella rope pull rod. In the direction of the line connecting the first end and the second end, the height dimension of the accommodating cavity is greater than the height dimension of the second annular recess. The action block is movably installed in the mounting through hole, the accommodating cavity is in communication with the mounting through hole, one end of the second elastic body is installed in the accommodating cavity and the other end abuts against the action block. The second limiting block is detachably installed in the second annular recess and abuts against the bottom of the action block.

[0008] Optionally, the first limiting block and the second limiting block are both formed in two, and the two first limiting blocks jointly enclose an annular structure to match the shape of the first annular recess. The two second limiting blocks jointly enclose an annular structure to match the shape of the second annular recess.

[0009] 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 comprises 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. The second part is formed in a plate structure and is used to abut against the end face of the barrel body close to the first end.

[0010] 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 of the second limiting block matches the outer wall shape of the second annular recess. The two end sides of the action block are formed in wedge surfaces which match the inner wall of the second limiting block to enable the action block to push the two second limiting blocks apart when the action block moves downward.

[0011] Optionally, the second elastic body is formed in a spring and is installed in the accommodating cavity. The automatic separation device of the parachute further comprises a guide rod. The guide rod comprises a rod body part and a limiting part connected to each other. The end of the rod body part away from the limiting part is installed in the accommodating cavity and penetrates the second elastic body. The end of the rod body part close to the limiting part is threadedly connected to the inner wall of the accommodating cavity. The radial dimension of the limiting part is greater than the radial dimension of the accommodating cavity, and the limiting part is used to abut against the second end.

[0012] Optionally, the first elastic body is provided 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.

[0013] Optionally, the parachute automatic separation device further comprises a damping baffle and two dampers, the damping baffle is sleeved on the first end, and the radial dimension of the damping baffle is greater than the radial dimension of the cylinder body, the two dampers are oppositely installed on the two sides of the cylinder body, and the damping baffle is configured to be in contact with the dampers.

[0014] Optionally, the parachute automatic separation device further comprises a U-shaped plate, two ends of the U-shaped plate are installed on the two sides of the cylinder body and correspond to the two dampers respectively, and the U-shaped plate is used for being connected with the aircraft.

[0015] Advantages:

[0016] 1. By the above technical scheme, first, the parachute automatic separation device can realize complete mechanical type, no external energy dependence automatic separation. Specifically, the parachute automatic separation device is composed of pure mechanical components (for example, the umbrella rope pull rod, the cylinder body, etc.), the energy source is the tension input transmitted by the parachute umbrella rope in the umbrella opening process, so that no external energy (can completely get rid of the dependence on the battery, the electronic control circuit, the electromagnet or the explosive bolt and other external energy or complex control system) is needed, and the device has high reliability (avoiding separation failure caused by circuit failure, signal interference, power consumption and the like, especially suitable for one-time use, long standby or harsh environment), in addition, the device has low cost and no use time limit (the core component is a mechanical structure, which is low in cost and can effectively avoid the disadvantages of explosive bolts and other one-time components).

[0017] Second, the parachute automatic separation device provides a double-stage locking (first-stage locking and second-stage locking) and unlocking mechanism, which can effectively prevent air mis-separation. Specifically, in the initial stage (before opening the umbrella), the first-stage locking is realized by the first limiting block being clamped in the first annular recess of the umbrella rope pull rod and being abutted against the end face of the cylinder body, and the elastic force of the first elastic body, mainly bearing the initial load before opening the umbrella; the second-stage locking is realized by the second limiting block being abutted against the stepped surface, mainly bearing the continuous tension of the parachute before landing after opening the umbrella. In this way, at the moment of opening the umbrella, the first-stage locking is first unlocked (the first limiting block is taken out), and the device enters the "pre-unlocking" state, but the second-stage locking quickly takes over the work and re-locks the device, and this process absorbs the impact of opening the umbrella, which can prevent the instantaneous failure of a single locking mechanism caused by the impact. At the same time, during the landing process, as long as the parachute provides a continuous upward tension, the second limiting block will be tightly clamped on the stepped surface, and the second locking mechanism will not have the problem of mis-unlocking. Thus, the problem of "pure mechanical structure causing mis-triggering due to elastic rebound or vibration" can be effectively solved.

[0018] Thirdly, the present application uses the mechanical change of the landing process as a trigger signal to realize automatic triggering. Specifically, the working logic of the present application is completely based on the force change, and the locking state of the second stage locking is dependent on the upward pulling force continuously borne by the umbrella rope pull rod and the clamping force between the step surface, the second limiting block and the umbrella rope pull rod to realize dynamic balance. In the air state, the second limiting block abuts against the step surface, and the device is locked. After landing, the pulling force disappears, the force balance is broken, and the downward elastic force of the first and second elastic bodies becomes the dominant force, respectively pushing the umbrella rope pull rod and the second limiting block to move downward to create conditions for unlocking. In this way, a mechanical "force sensor" is created, which can automatically sense the air state and the landing state and automatically realize separation, and can effectively overcome the defects of the prior art "depending on manual intervention or specific terrain conditions".

[0019] Fourthly, the present application is highly integrated in structure and has a clever action logic. Specifically, all functional components are integrated in the working cavity of the barrel body, and through the stepped cavity (first cavity, second cavity and third cavity) design, the track of the limiting block movement and the locking step surface are naturally formed, and the upward and downward movement of the pull rod links all the actions of the components. In this way, all functions are completed in a cylindrical mechanism, which has small overall volume, light weight, compact structure and is easy to install and arrange on the aircraft. In addition, the series of actions such as upward movement of the pull rod, compression of the first elastic body, formation of the second locking mechanism, downward movement of the pull rod and disengagement of the second limiting block are closely linked, the logic is clear and the reliability is high. This "one-rod driving" design simplifies the structure and reduces the number of parts.

[0020] Overall, the present application successfully produces a series of positive technical effects through the pure mechanical double-locking mechanism and the trigger mechanism based on mechanical balance: not only saves external energy, but also greatly improves the reliability, and in addition, effectively prevents in-air mis-separation and realizes automatic separation after landing.

[0021] 2. Other beneficial effects or advantages of the present application will be described in detail in the specific embodiments. BRIEF DESCRIPTION OF DRAWINGS

[0022] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiment description. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without creative labor.

[0023] Among them:

[0024] Figure 1is a perspective view of an automatic parachute separation device according to an exemplary embodiment of the present application;

[0025] Figure 2 is an exploded view of an automatic parachute separation device according to an exemplary embodiment of the present application;

[0026] Figure 3 is Figure 2 is an enlarged view of a partial structure at A in FIG. 1;

[0027] Figure 4 is a cross-sectional view of a barrel according to an exemplary embodiment of the present application;

[0028] Figures 5 to 9 is a schematic view of a separation process of an automatic parachute separation device according to an exemplary embodiment of the present application, wherein, Figure 5 is a schematic view of an initial locking state of an automatic parachute separation device, Figure 6 is a schematic view of a first limiting block being released at a beginning of parachute opening, Figure 7 is a schematic view of a buffer stage during parachute opening, Figure 8 is a schematic view of a second limiting block being displaced out of a barrel during parachute opening, Figure 9 is a schematic view of the second limiting block being released during parachute opening.

[0029] Reference numerals in the drawings:

[0030] 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 - accommodating cavity; 2 - barrel; 21 - working cavity; 211 - first cavity; 212 - second cavity; 213 - third cavity; 3 - first limiting block; 31 - first portion; 32 - second portion; 41 - first elastic body; 42 - second elastic body; 5 - action block; 51 - wedge surface; 6 - second limiting block; 7 - guide rod; 71 - rod body portion; 72 - limiting portion; 81 - damping baffle; 82 - damper; 9 - U-shaped plate. DETAILED DESCRIPTION

[0031] The technical solutions of the present application will be described in detail below with reference to the accompanying drawings.

[0032] As Figures 1 to 9As shown, the present application provides a parachute automatic separation device 100, comprising a canopy line pull rod 1, a barrel 2, a first limiting block 3, a first elastic body 41, a second elastic body 42, an action block 5 and a second limiting block 6, the barrel 2 is formed with a through working cavity 21, the canopy line pull rod 1 is arranged in the working cavity 21, the canopy line pull rod 1 comprises a first end 11 and a second end 12 arranged oppositely, the first end 11 is used for connecting with the parachute, one end of the barrel 2 away from the first end 11 is used for connecting with the aircraft, the first end 11 is formed with a first annular recess 111, the first limiting block 3 is arranged in the first annular recess 111 detachably, and the first limiting block 3 is used for abutting against the end face of the barrel 2 close to the first end 11, the working cavity 21 comprises a first cavity 211, a second cavity 212 and a third cavity 213 distributed and communicated in sequence 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;

[0033] The second end 12 is formed with a second annular recess 121 and a mounting through hole 122 arranged in the radial direction of the canopy line pull rod 1, the end face of the second end 12 is recessed inwardly to form an accommodating cavity 123 extending in the axial direction of the canopy line pull rod 1, in the direction of the connecting line of the first end 11 and the second end 12, the height dimension of the accommodating cavity 123 is greater than the height dimension of the second annular recess 121, the action block 5 is movably installed in the mounting through hole 122, the accommodating cavity 123 is communicated with the mounting through hole 122, one end of the second elastic body 42 is installed in the accommodating cavity 123 and the other end abuts against the action block 5; the second limiting block 6 is detachably installed in the second annular recess 121 and abuts against the bottom of the action block 5.

[0034] In order to make the present application clear and accurate for the skilled in the art, the working process / working principle of the parachute automatic separation device 100 of the present application is described below in combination with the drawings.

[0035] In the initial state, that is, when the parachute is not opened (see Figure 5 As shown), at this time, the parachute canopy line is connected with the canopy line pull rod 1, and the barrel 2 is connected with the aircraft. In the parachute opening starting stage (as 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.

[0036] 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.

[0037] 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.

[0038] 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, no pulling force is applied to the parachute rope pull rod 1 again, the first elastic body 41 will push the second limiting block 6 to move downward, and the parachute rope pull rod 1 will also move downward, so that the second limiting block 6 will be pushed out of the barrel 2 after a certain period of time, and then the second elastic body 42 continues to push the action block 5 to move downward, as shown, at this time, the action block 5 will push the second limiting block 6 to disengage, thereby completing the unlocking of the parachute rope pull rod 1 and the barrel 2, that is, completing the unlocking of the parachute and the aircraft. Figure 9

[0039] Through the above technical scheme, first, the present application can realize complete mechanical type, no external energy dependent automatic separation. Specifically, the parachute automatic separation device 100 of the present application is composed of pure mechanical components (for example, the parachute rope pull rod 1, the barrel 2, etc.), the source of its energy is the pulling force input transmitted by the parachute rope during the parachute opening process, so that not only can it be free of external energy (can completely get rid of the dependence on battery, electric control circuit, electromagnet or explosive bolt, etc. external energy or complex control system), but also has high reliability (avoiding separation failure caused by circuit failure, signal interference, power consumption, etc. especially suitable for one-time use, long standby or harsh environment), in addition, it also has low cost and no use time limit (the core component is a mechanical structure, which is low in cost. Can effectively avoid the disadvantages of explosive bolts and other one-time components).

[0040] Second, the present application provides a two-stage locking (first-stage locking and second-stage locking) and unlocking mechanism, which can effectively prevent air separation. Specifically, in the initial stage (before opening the parachute), the first-stage locking is realized by the first limiting block 3 being clamped in the first annular recess 111 of the parachute rope pull rod 1 and being abutted against the end face of the barrel 2, and the elastic force of the first elastic body 41, mainly bearing the initial load before opening the parachute; the second-stage locking is realized by the second limiting block 6 being abutted against the stepped surface, mainly bearing the continuous pulling force of the parachute before landing after opening the parachute. In this way, at the moment of opening the parachute, the first-stage locking is first released (the first limiting block 3 is brought out), and the device enters the "pre-unlocking" state, but the second-stage locking quickly takes over the work and relocks the device, this process absorbs the impact of opening the parachute, which can prevent the instantaneous failure of a single locking mechanism caused by impact. At the same time, during the landing process, as long as the parachute provides continuous upward pulling force, the second limiting block 6 will be tightly clamped on the stepped surface, and the second locking mechanism will not have the problem of false unlocking. Thus, the problem of "pure mechanical structure causing false triggering due to elastic rebound or vibration" can be effectively solved.

[0041] ​Thirdly, the present application uses the mechanical change of the landing process as a trigger signal to realize automatic triggering. Specifically, the working logic of the present application is completely based on the force change, and the locking state of the second stage locking is dependent on the upward pulling force continuously borne by the umbrella rope pull rod 1 and the clamping force between the step surface, the second limiting block 6 and the umbrella rope pull rod 1 to realize dynamic balance. In the air state, the second limiting block 6 abuts against the step surface, and the device is locked. After landing, the pulling force disappears, the force balance is broken, and the downward elastic force of the first and second elastic bodies 41 and 42 becomes the dominant force, respectively pushing the umbrella rope pull rod 1 and the second limiting block 6 to move downward to create conditions for unlocking. In this way, a mechanical "force sensor" is created, which can automatically sense the air state and the landing state and automatically realize separation, and can effectively overcome the defects of the prior art "depending on manual intervention or specific terrain conditions".

[0042] Fourthly, the present application is highly integrated in structure, and the action logic is ingenious. Specifically, all functional components are integrated in the working cavity 21 of the barrel 2. Through the stepped cavity (the first cavity 211, the second cavity 212 and the third cavity 213) design, the limiting block movement track and the locking step surface are naturally formed, and the upward and downward movement of the umbrella rope pull rod 1 serially connects the actions of all components. In this way, all functions are completed in a cylindrical mechanism, the overall volume is small, the weight is light, the structure is compact, and it is easy to install and arrange on the aircraft. Moreover, the upward movement of the pull rod, the compression of the first elastic body 41, the formation of the second locking mechanism, the downward movement of the pull rod, the escape of the second limiting block 6 and a series of actions are closely linked, the logic is clear, and the reliability is high. This "one-rod driving" design simplifies the structure and reduces the number of parts.

[0043] Overall, the present application successfully produces a series of positive technical effects through the pure mechanical double-locking mechanism and the trigger mechanism based on mechanical balance: not only saves external energy, but also greatly improves the reliability, and in addition, effectively prevents air separation and realizes automatic separation after landing.

[0044] In one embodiment of the present application, as shown in Figure 2 , Figures 5 to 9 The first limiting block 3 and the second limiting block 6 of the present application are both formed into two, the two first limiting blocks 3 are collectively enclosed into a ring structure to match the shape of the first annular recess 111, and the two second limiting blocks 6 are collectively enclosed into a ring structure to match the shape of the second annular recess 121.

[0045] Thus, by setting the first limiting block 3 and the second limiting block 6 as such, first, the first limiting block 3 and the second limiting block 6 are respectively set as two and enclosed into a ring shape, so that the locking force can be symmetrically and uniformly applied to the first end 11 (the first annular recess 111) and the second end 12 (the second annular recess 121). This symmetrical layout avoids eccentric force or stress concentration that a single block body can generate, ensures the stability of the locked state, and reduces the risk of accidental loosening due to uneven force.

[0046] Second, the first limiting block 3 and the second limiting block 6 are respectively designed as two block bodies, which can provide the necessary conditions for radial movement. When unlocking is needed, the two separate block bodies can be synchronously and smoothly separated radially to the two sides, thereby being removed from the corresponding annular recesses to complete the unlocking action. This design also facilitates folding the two block bodies inward from the outside when resetting, and reassembling them to the corresponding recess positions, which is more convenient to operate.

[0047] Third, compared with machining a complete sleeve-shaped part with an inner tapered surface, manufacturing two block parts with relatively simple shapes is more easily achieved in terms of process and lower in cost. Moreover, when assembling, the two block bodies can be combined and placed into the corresponding cavities or recesses, which can also effectively reduce the assembly difficulty.

[0048] In an embodiment of the present application, as shown in Figure 2 the radial size of the first annular recess 111 gradually increases in the direction from the second end 12 to the first end 11; the first limiting block 3 includes a first portion 31 and a second portion 32 connected to each other, the shape of the first portion 31 matches the shape of the first annular recess 111, and the second portion 32 is formed as a plate structure and used to abut against the end face of the cylinder body 2 close to the first end 11.

[0049] Thus, by setting the first annular recess 111 and the corresponding first limiting block 3 as such, first, reliable self-locking and smooth unlocking can be achieved. The first annular recess 111 is designed as a structure with gradually increasing radial size (i.e., tapered or V-shaped), which matches the first portion 31 of the first limiting block 3, and can form a bevel self-locking mechanism. Thus, when locking, when the umbrella rope pull rod 1 is subjected to an upward pulling force, the bevel structure can effectively convert the axial pulling force into a force that forces the first limiting block 3 to be radially compressed, so that the locking is more secure and prevents it from loosening in vibration; at the same time, when unlocking, only a relatively small force is needed to move the first limiting block 3 radially outward a little, which can break the self-locking state, and then the umbrella rope pull rod 1 can be easily moved upward, so that the first portion 31 slides out of the recess, achieving smooth and labor-saving unlocking.

[0050] Second, the second part 32 is arranged as a plate structure and abuts against the end face of the cylinder 2. In this way, not only can the bearing area be effectively increased and the pressure be dispersed to avoid damage or deformation of the end face of the cylinder 2 or the limiting block under high pressure, but also the durability and reliability of the device are improved, and the final position of the first limiting block 3 in the locked state can be determined, the over-embedded or uncertain position of the first limiting block 3 can be effectively prevented, and the stability of the axial limiting effect is ensured.

[0051] In an embodiment of the present application, as shown in Figure 3 the radial dimension of the second annular recess 121 gradually increases in the direction from the first end 11 to the second end 12, the inner wall shape of the second limiting block 6 is matched with the outer wall shape of the second annular recess 121, and the two end sides of the action block 5 are formed as wedge surfaces 51 matched with the inner wall of the second limiting block 6, so that the two second limiting blocks 6 can be pushed apart from each other when the action block 5 moves downward.

[0052] In this way, through the arrangement of the second annular recess 121 and the action block 5, first, the same inclined surface self-locking mechanism as the first locking stage (see the inclined surface self-locking principle of the first annular recess 111 above) can be realized. When the parachute is opened, the tension of the parachute lines is transmitted through the line rod 1, which will force the action block 5 to drive the second limiting block 6 to move upward and abut against the step surface. At this time, the upward force will act on the inclined surface of the second limiting block 6, which will be pressed radially inward, so that it is more firmly clamped in the second annular recess 121. This design can ensure the stability of the second stage locking when bearing the continuous upward tension, and greatly enhance the locking reliability of the device during the period from opening to landing.

[0053] Second, the second limiting block 6 can be smoothly and reliably unlocked after landing. Specifically, when the parachute lines are no longer axially compressed after landing, the downward force of the second elastic body 42 acting on the action block 5 will be converted into a force pushing the two second limiting blocks 6 radially outward through the matched wedge surfaces 51, so that they are smoothly separated from the second annular recess 121, thereby completing the final unlocking. This design of automatically converting axial movement into radial movement by using mechanical inclined surface can ensure the automaticity and reliability of the separation action without any external intervention.

[0054] In an embodiment of the present application, as shown in Figure 2 , Figures 5 to 9As shown, the second elastic body 42 of the present application can be formed as a spring and installed in the accommodating cavity 123; the parachute automatic separation device 100 further comprises a guide rod 7, which comprises a rod body part 71 and a limiting part 72 connected with each other, the rod body part 71 is installed in the accommodating cavity 123 and passes through the second elastic body 42 at one end away from the limiting part 72, the outer wall of the end of the rod body part 71 close to the limiting part 72 is threadedly connected with the inner wall of the accommodating cavity 123, the radial dimension of the limiting part 72 is greater than that of the accommodating cavity 123, and the limiting part 72 is used to abut against the second end 12.

[0055] Thus, first, the accommodating cavity 123 formed can provide installation space for the second elastic body 42, which is an embedded design, and can effectively avoid additional increase of structural length or volume outside the barrel 2 to arrange the spring, greatly optimizing the utilization of internal space, so that the axial structure of the whole device is more compact and small.

[0056] Second, the guide rod 7 passes through the inside of the accommodating cavity 123 and the second elastic body 42, constituting a precise guide mechanism. This mechanism can ensure that the elastic force generated by the second elastic body 42 during compression and release is strictly transmitted in the axial direction, preventing the spring from bending, offloading or jamming, ensuring the precision and consistency of the direction of the force, so that the movement of the action block 5 is more reliable and smooth.

[0057] Third, the threadedly connected rod body part 71 also facilitates the installation, replacement and maintenance of the guide rod 7 and the second elastic body 42.

[0058] In an embodiment of the present application, as shown, Figures 5 to 9 The first elastic body 41 of the present application can be provided 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.

[0059] Thus, first, the first elastic body 41 is specifically defined as a spring, which clearly defines its properties as a reliable and linearly good elastic element, which can ensure that it can provide predictable and consistent elastic force when compressed and released, and is the basis for the device to realize the timing trigger 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 corresponding inner wall of the second cavity 212, which can play a guiding role to effectively prevent the spring from bending, instability or jamming during compression, ensuring that the force is always transmitted in the axial direction, thereby ensuring the accurate and reliable movement trajectory of the second limiting block 6 and the parachute rope rod 1 assembly.

[0060] Second, it can ensure that the first elastic body 41 will not be in radial friction or collision with the step surface of the third cavity 213 or other structures during the entire movement process. This precise space planning can avoid additional resistance, wear or functional failure caused by unnecessary contact between parts, making the movement of internal moving parts of the device more smooth and efficient.

[0061] In an embodiment of the present application, as shown in Figure 1 , Figure 2 , Figures 5 to 9 The parachute automatic separation device 100 of the present application can also 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 greater than the radial dimension of the barrel 2, the two dampers 82 are oppositely installed on the two sides of the barrel 2, and the damping baffle 81 is configured to be in contact with the dampers 82.

[0062] In this embodiment, in the air (as shown in Figure 7 ), at the moment when the parachute cord is straightened, due to the elasticity of the parachute cord, the parachute cord pull rod 1 will have a short moment when it no longer bears upward force, at this moment, the first elastic body 41 will push the second limiting block 6 and the parachute cord pull rod 1 to move downward, the damping baffle 81 will contact the damper 82, and the damper 82 will slow down the speed of the parachute cord pull rod 1 moving downward, so as to avoid the second limiting block 6 from being pulled out in the air.

[0063] In this way, first, during the opening of the parachute, after the parachute cord is straightened, there may be a moment when the tension decreases due to elasticity. At this moment, the first elastic body 41 will push the parachute cord pull rod 1 assembly to move downward. The damping baffle 81 will contact the damper 82 as the pull rod moves downward. The damper 82 significantly slows down the speed of the parachute cord pull rod 1 moving downward by providing resistance (such as friction, oil damping force, etc.). This delay ensures that the downward stroke is not enough to make the second limiting block 6 come off the step surface. Subsequently, the continuous tension of the parachute cord will pull the pull rod up again, and the device will return to the locked state. Thus, it can effectively avoid premature separation caused by tension fluctuations in the air.

[0064] Second, this design is a "smart" 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 short downward movement is inhibited by the damper 82. When landing, the tension of the parachute cord disappears, and the first elastic body 41 will push the assembly to continue moving downward. Although the initial speed is slowed down by the damper 82, the continuous elastic force will eventually overcome the damping force, ensuring that the second limiting block 6 has enough time and force to complete the final disengagement action, thereby ensuring that the separation function will eventually trigger.

[0065] In an embodiment of the present application, as shown in Figure 1 , Figure 2 and Figure 7As shown, the parachute automatic separation device 100 of the present application can further comprise a U-shaped plate 9, both ends of which are mounted on both sides of the barrel 2 and correspond to the two dampers 82 respectively, and the U-shaped plate 9 is used for connecting with the aircraft.

[0066] In this way, first, the barrel 2 can focus on its core function (housing the locking and separation mechanism), without the need to design complex mounting points on its body, simplifying the structure and manufacturing of the barrel 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.

[0067] Second, both ends of the U-shaped plate 9 are mounted on both sides of the barrel 2 and correspond to the dampers 82, which is equivalent to adding a solid "stiffening beam" or "mounting bridge" at the location of the dampers 82. When the dampers 82 work (especially when impacted by the damping baffle 81), the U-shaped plate 9 can effectively disperse and absorb these local loads, preventing them from being completely borne by the barrel 2 wall. This enhances the stiffness and strength of the damper 82 mounting point, reducing the risk of deformation or damage under vibration or impact, ensuring the long-term reliability of the damping function.

[0068] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited thereto, any change or replacement within the technical scope disclosed by the present application should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. An automatic parachute release device, characterized by The utility model provides umbrella rope pull rod (1), cylinder (2), first limit block (3), first elastic body (41), second elastic body (42), action block (5) and second limit block (6), the cylinder (2) is formed with the work cavity (21) that penetrates, the umbrella rope pull rod (1) is worn in the work cavity (21), the umbrella rope pull rod (1) includes the first end (11) and second end (12) of opposite arrangement, the first end (11) is used for connecting with parachute, the cylinder (2) is used for connecting with aircraft away from the first end (11) one end, the first end (11) forms the first annular recess (111), the first limit block (3) is detachably arranged in the first annular recess (111), and the first limit block (3) is used for with the end face of cylinder (2) close to the first end (11) and butts, the work cavity (21) includes first cavity (211), second cavity (212) and third cavity (213) that distribute and communicate in sequence along the direction from the first end (11) to the second end (12), the radial dimension of third cavity (213) is greater than the radial dimension of second cavity (212), the radial dimension of second cavity (212) is greater than the radial dimension of first cavity (211), one end of first elastic body (41) is installed in the second cavity (212), and the other end of first elastic body (41) extends to the third cavity (213) and butts with second limit block (6); The second end (12) is formed with the second annular recess (121) and the installation through -hole (122) that penetrates along the radial direction of the umbrella rope pull rod (1) on the peripheral wall, the end face of the second end (12) is recessed inwards and forms the accommodating cavity (123) that extends along the axial direction of the umbrella rope pull rod (1), in the direction of the connecting line of the first end (11) and the second end (12), the height dimension of the accommodating cavity (123) is greater than the height dimension of the second annular recess (121), the action block (5) is movably installed in the installation through -hole (122), the accommodating cavity (123) is communicated with the installation through -hole (122), one end of second elastic body (42) is installed in the accommodating cavity (123) and the other end butts with the action block (5);Second limit block (6) is detachably installed in the second annular recess (121) and butts with the bottom of action block (5).

2. The automatic parachute deployment apparatus of claim 1, wherein The first limit block (3) and the second limit block (6) are formed into two, two first limit blocks (3) are enclosed into annular structure to mutually match the shape of the first annular recess (111), two second limit blocks (6) are enclosed into annular structure and mutually match the shape of the second annular recess (121).

3. An automatic parachute deployment device according to claim 2, wherein 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) comprises a first part (31) and a second part (32) connected with 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) close to the first end (11).

4. The automatic parachute deployment apparatus of claim 2, wherein, 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 of the second limiting block (6) matches the shape of the outer wall of the second annular recess (121), and the two end sides of the action block (5) are formed as wedge surfaces (51) which match the inner wall of the second limiting block (6) to enable the two second limiting blocks (6) to be pushed apart from each other when the action block (5) moves downward.

5. An automatic parachute deployment device according to claim 4, wherein The second elastic body (42) is formed as a spring and is installed in the accommodating cavity (123); the parachute automatic separation device further comprises a guide rod (7) comprising a rod body part (71) and a limiting part (72) connected with each other, one end of the rod body part (71) away from the limiting part (72) is installed in the accommodating cavity (123) and penetrates the second elastic body (42), the outer wall of one end of the rod body part (71) close to the limiting part (72) is threadedly connected with the inner wall of the accommodating cavity (123), the radial dimension of the limiting part (72) is greater than the radial dimension of the accommodating cavity (123), and the limiting part (72) is used to abut against the second end (12).

6. The automatic parachute deployment apparatus of claim 1, wherein The first elastic body (41) is provided 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 deployment apparatus of claim 1, wherein The parachute automatic separation device further comprises a damping baffle (81) and two dampers (82), the damping baffle (81) is sleeved on the first end (11), the radial dimension of the damping baffle (81) is greater than the radial dimension of the cylinder (2), and the two dampers (82) are oppositely installed on the two sides of the cylinder (2), and the damping baffle (81) is configured to be capable of contacting the dampers (82).

8. An automatic parachute deployment device according to claim 7, characterised in that, The parachute automatic separation device further comprises a U-shaped plate (9), both ends of the U-shaped plate (9) are installed on the two sides of the cylinder (2) and correspond to the two dampers (82) respectively, and the U-shaped plate (9) is used to be connected with an aircraft.

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