Linear connector for aircraft, safety device, aircraft equipped with safety device, and fastening method using linear connector for aircraft

Abstract

To provide a linear connection tool for an air vehicle which can connect with an object to be deployed (a deployed object) without using a connection tool, such as a carabiner, and to provide a safety device which ejects the deployed object with which the linear connection tool for the air vehicle is connected, an air vehicle including the safety device, and a tying method using the linear connection tool for the air vehicle.SOLUTION: A safety device includes: an actuator; a push-up member which is pushed up in one direction by the actuator; a deployed object which is pushed up while supported by a support part of the push-up member; and a housing container which houses the push-up member and the deployed body therein and has a bottomed cylindrical shape. The other end of a linear connection tool 80 for an air vehicle, which is connected at one end to an arm 34 of an airframe 31 of an air vehicle, is connected to the other end 70b of a bridle line 70 connected to a line connected to the deployed body. The linear connection tool 80 for the air vehicle includes: a linear member 81; and an annular member 83 connected to a loop structure 82 formed at one end of the linear member 81.SELECTED DRAWING: Figure 6

Description

[Technical Field]

[0001] The present invention relates to a linear connector for an aircraft, a safety device for launching a projectile such as a parachute or paraglider to which the linear connector for an aircraft is connected, an aircraft equipped with the safety device, and a fastening method using the linear connector for an aircraft. [Background technology]

[0002] In recent years, with the development of autonomous control technology and flight control technology, the industrial use of aircraft equipped with multiple rotors, such as drones, has been accelerating. Drones fly, for example, by simultaneously rotating multiple rotors in a balanced manner. Ascending and descending can be achieved by increasing or decreasing the rotation speed of the rotors, and forward and backward movement can be achieved by tilting the aircraft through increasing or decreasing the rotation speed of the rotors. Such aircraft are expected to become more widespread worldwide in the future.

[0003] However, the risk of aircraft falling accidents such as those described above is considered dangerous and is hindering the widespread use of aircraft. To reduce the risk of such accidents, parachute devices for aircraft are being commercialized as safety devices.

[0004] For example, the applicant has filed a patent application for the parachute safety device described below in Patent Document 1. As shown in FIG. 1 of Patent Document 1, the safety device of Patent Document 1 includes a piston member (sliding member), a cylinder that houses the piston member and has a hole through which the piston member protrudes outward when activated, a push-up member that is pushed up in one direction by the piston member, a projectile that is supported and pushed up by the push-up member, a gas generator that moves the piston member within the cylinder, and a container that houses the projectile or the like. The push-up member has a support portion that is located on the distal end of the piston member relative to the tip of the piston member in the direction of movement of the piston member. The bottom of the push-up member is fixed to the tip of the piston member. When the projectile is a parachute or the like, the other end of a string-like connecting member called a line that is connected to one end of the parachute is connected to the container or the flying vehicle. [Prior art documents] [Patent documents]

[0005] [Patent Document 1] Japanese Patent Publication No. 2020-1680 Summary of the Invention [Problem to be solved by the invention]

[0006] In a safety device such as that described in Patent Document 1, it is easier to attach the line to the aircraft after the safety device container is fixed to the aircraft. In this case, to further facilitate the work of attaching the line to the aircraft, the other end of the line may be brought outside the container in advance and connected to the other end of a string-like connector, one end of which is connected to the aircraft, via a connector such as a carabiner.

[0007] However, when a carabiner or other connector is used on a flying object, the total weight of the flying object increases compared to when no connector is used. Furthermore, since the strength of the connector must be strong enough to withstand the parachute deployment, it is difficult to reduce the weight. Furthermore, when a metal carabiner is used as a connector in consideration of strength, there is a risk of breakage due to friction between the various components of the parachute and the carabiner (especially the sharp corners of the carabiner).

[0008] Therefore, the present invention aims to provide a linear connector for an aircraft that can be connected to a deployed object such as a parachute or paraglider without using a connector such as a carabiner, a safety device that launches a projectile such as a parachute or paraglider to which the linear connector for an aircraft is connected, an aircraft equipped with the safety device, and a fastening method using the linear connector for an aircraft. [Means for solving the problem]

[0009] (1) The linear connector for an aircraft according to the present invention is capable of being connected by tying one end to a part of an aircraft equipped with a safety device, and is capable of being connected to a deployable body included in the safety device or a line connected to the deployable body directly at the other end, and is comprised of a ring member and a loop structure formed by passing the tip end through the inside of the ring member, folding it back, and fixing the tip end to a midpoint. The aforementioned and a linear member having at one end a connection portion formed at the other end that can be directly connected to the deployable body or a line connected to the deployable body, wherein the inner periphery of the loop structure is formed to a size that allows for the passage of another loop structure that is temporarily formed by folding back at a midpoint between one end and the other end of the linear member, and the outer periphery of the annular member is formed to a size that allows for the passage of the inner periphery of the other loop structure.

[0010] (2) In the linear connector for a flying object according to (1) above, when the distance from the geometric center of the annular member to the outermost peripheral portion closest thereto is R and the length when the loop structure is stretched the most by the annular member is L, it is preferable that the relationship L < R holds.

[0011] (3) In the linear connector for a flying object according to (2) above, when the width of the linear member is W, it is preferable that the relationship W < L < R holds.

[0012] (4) The safety device according to the present invention includes an ejection unit that ejects an ejectile, a container that houses the ejection unit and encloses the ejection unit, and a line having one end connected to the ejectile, and the other end of the line is the other end directly connected to the linear connector for a flying object according to any one of (1) to (3) above.

[0013] [[ID=B15]](5) In the safety device according to (4) above, it further preferably includes an abnormality detection device capable of detecting an abnormality in the flying object or the surrounding environment, and the abnormality detection device preferably activates the ejection unit when detecting the abnormality.

[0014] (6) In the safety device according to (5) above, when the abnormality is detected by the abnormality detection device, it preferably further includes a flight control unit that stops a propulsion device provided on the flying object.

[0015] (7) The flying object according to the present invention is characterized by including an airframe, the safety device according to any one of (4) to (6) above provided on the airframe, and one or more propulsion mechanisms coupled to the airframe and propelling the airframe.

[0016] (8) The present invention is a tying method for tying the linear connector for a flying object according to any one of (1) to (3) above, which can be connected to the end of a line connected to a deployable object, to a part of a flying object. the other end of the linear connector for a flying object according to any one of (1) to (3) above that can be connected to the one end is tied to a part of a flying object, and the one enda step of winding the wire around a part of the aircraft; the other end and the one end and forming a temporary loop structure by folding back the loop structure at a midpoint between the Inner circumference of The other loop structure of a step of passing the inner periphery of the other loop structure through the annular member so that the annular member passes through the inner periphery of the other loop structure; a step of moving the tip of the other loop structure to the position of the loop structure, and then connecting the linear member to the linear connector for the aircraft; the other end pulling the cord to the side, tightening and tying it down. Mumo That is why. [Effects of the Invention]

[0017] According to the present invention, it is possible to provide a linear connector for an aircraft that can be connected to a deployed object such as a parachute or paraglider without using a connector such as a carabiner, a safety device that launches a projectile such as a parachute or paraglider to which the linear connector for an aircraft is connected, an aircraft equipped with the safety device, and a fastening method using the linear connector for an aircraft. [Brief explanation of the drawings]

[0018] [Figure 1] 1 is a cross-sectional view showing an initial state of a safety device according to an embodiment of the present invention. [Figure 2] FIG. 2 is a cross-sectional view showing the safety device of FIG. 1 in an operating state. [Figure 3] FIG. 2 is a perspective view showing only a container used in the safety device of FIG. 1. [Figure 4] 2A and 2B are diagrams showing only the linear connector for an aircraft used in the safety device of FIG. 1, in which (a) is a plan view and (b) is a side view. [Figure 5] FIG. 2 is a schematic diagram showing the flying body to which the safety device (initial state) of FIG. 1 is attached. [Figure 6] 6 is a partially enlarged view of one specific example of the flying vehicle of FIG. 5. [Figure 7]FIG. 7 is a perspective view showing a state in which the safety device of the flying object of FIG. 6 is in the middle of operation. [Figure 8] FIG. 7 is a partial cross-sectional view showing the state after the safety device of the flying object of FIG. 6 has been activated. [Figure 9] 7(a) is a development view of a pocket provided on the outside of the container in the safety device of FIG. 6, and FIG. 7(b) is a folded view. [Figure 10] 5 is a diagram illustrating a process of attaching the linear connector for an aircraft of FIG. 4 to the aircraft. FIG. [Figure 11] 5 is a diagram illustrating a process of attaching the linear connector for an aircraft of FIG. 4 to the aircraft. FIG. [Figure 12] 5 is a diagram illustrating a process of attaching the linear connector for an aircraft of FIG. 4 to the aircraft. FIG. [Figure 13] FIG. 2 is a block diagram showing the functional configuration of the safety device of FIG. 1. [Figure 14] FIG. 10 is a side view of an aircraft equipped with a safety device including a modified ejection device. [Figure 15] FIG. 10 is a side view of an aircraft equipped with a safety device including a modified ejection device. [Figure 16] FIG. 10 is a schematic cross-sectional view of a safety device including a modified ejection device. DETAILED DESCRIPTION OF THE INVENTION

[0019] A safety device and an aircraft according to an embodiment of the present invention will be described below with reference to FIGS.

[0020] As shown in FIG. 1 , the safety device 100 includes an actuator 1, a lifting member 15 that is lifted in one direction (upward in FIG. 1 ) by the actuator 1, a projectile 16 that is supported and lifted by the lifting member 15, a cylindrical container 18 with a bottom that houses the actuator 1, the lifting member 15, and the projectile 16, and a lid 21 that closes the open end of the container 18. In this embodiment, the projectile 16 is a deployable object such as a parachute or paraglider. A blocking member 60 is provided in the gap between the container 18 and the lid 21 to prevent the intrusion of liquids, dust, and the like. Examples of the blocking member 60 include any material that is waterproof and dustproof, such as an O-ring, a cured resin, or a foam material. As a variation of the blocking member 60, a film-like material may be used to wrap at least the edge of the lid 21 and the side of the container 18.

[0021] Parachutes, which are an example of a deployable object that can be used in this embodiment, may be of various types, such as "FLAT CIRCULAR", "CONICAL", "BICONICAL", "TRICONICAL", "EXTENDED SKIRT", "HEMISPHERICAL", "GUIDE SURFACE", "ANNULAR", "CROSS", "FLAT RIBBON", "CONICAL RIBBON", "RIBBON", "RINGSLOT", "RING SAIL", "DISC-GAP-BAND", "ROTAFOIL", "VORTEX RING", and "SANDIA RFD". Examples include "RFD", "PARACOMMANDER", "PARAWING", "PARAFOIL", "SAILWING", "VOLPLANE", and "BALLUTE".

[0022] The actuator 1 comprises a piston member 10 which is a sliding member, a cylinder 14 which houses the piston member 10 and has a hole 13 through which the piston member 10 protrudes outward (upward in Figures 1 and 2) when actuated, a base 2 (squib holder) to which one end of the cylinder 14 is crimped and which is attached via a hole 25 in the center of the bottom inside the container 18, and a gas generator (such as a micro gas generator) 17 which serves as a power source for moving the piston member 10 within the cylinder 14.

[0023] The base 2 comprises an approximately cylindrical member 2A that holds a gas generator 17 on the cylinder 14 side, which generates power to slide the piston member 10, and a flange portion 2B provided on the opposite side of the approximately cylindrical member 2A from the cylinder 14 side.

[0024] The flange portion 2B is machined into a generally U-shaped, horseshoe-like shape (not shown), and includes a plurality of holes 2a used for attachment to the container 18, a plurality of fixing holes (not shown) used for attachment to the airframe 31 of the flying vehicle 30 (described later), and an insertion opening 2c used for inserting an energizing connector 22 into the lower electrode 17b of the gas generator 17. The inner wall of the holes 2a is internally threaded so that a bolt 28 (described later) can be screwed into the hole. The inner wall of the fixing holes (not shown) is also internally threaded so that a bolt (not shown) can be screwed into the flying vehicle 30 (described later) from the airframe 31 side, thereby fixing the base 2 to the airframe 31.

[0025] The connector 22 includes a main body 22a that can be inserted into the substantially cylindrical member 2A through the insertion opening 2c, a protrusion (not shown) protruding from the side surface of the lower part of the main body 22a, and a hole 22c into which the electrode 17b located inside the substantially cylindrical member 2A is inserted. The protrusion (not shown) is electrically connected to a connector (not shown) that is connected to an external power source via a wiring (not shown) that extends in a direction perpendicular to the insertion direction of the connector 22 (when attached to the base 2, along the radial direction from the center of the base 2). The main body 22a also has a hole 22c formed therein that is electrically connected to both the electrode 17b and the wiring (not shown) that is connected to the protrusion (not shown).

[0026] In addition, the insertion port 2c of the base 2 and the connector 22 are configured so that when attached to the base 2, they extend radially from the center of the base 2 so that the above-mentioned wiring (not shown) can be arranged so as not to block the hole portion 24.

[0027] The piston member 10 has a main body portion 10a having an outer diameter approximately the same as the inner diameter of the cylinder 14, a rod-shaped portion 10b connected to the main body portion 10a, extending upward, and having a smaller diameter than the main body portion 10a, a hole portion 10c provided inside the main body portion 10a and the rod-shaped portion 10b, a female thread portion 10d provided at the upper end of the rod-shaped portion 10b, and a groove portion 10e provided circumferentially around the main body portion 10a.

[0028] At least the upper end of the rod-shaped portion 10b has a non-circular cross section, although this is not shown. Here, a non-circular shape refers to, for example, a polygonal, elliptical, star-shaped, or gear-shaped shape, but any non-circular shape is included. The tubular member 4 is fitted or loosely fitted to the lower part of the rod-shaped portion 10b, with one end of the tubular member 4 in contact with the main body 10a. A gap may exist between the inner wall of the tubular member 4 and the outer wall of the rod-shaped portion 10b, but this gap need only be large enough not to interfere with plastic deformation due to substantially uniform compression during a collision, as described below.

[0029] 1 and 2, the tubular member 4 is held by the holding member 5 at the bottom of the rod-shaped portion 10b with one end in contact with the main body portion 10a. The tubular member 4 is made of a material that undergoes plastic deformation and has a lower tensile strength than the piston member 10 and the stopper member 23 described below (e.g., metals such as iron, aluminum, brass, copper, alloys such as stainless steel, resins, etc.) (e.g., metals such as aluminum and brass, alloys such as stainless steel, resins such as monomer cast nylon, polyamide synthetic resins such as nylon 6, nylon 6,6, and nylon 4,6, etc.). The holding member 5 may be an elastic member such as rubber or made of the same material as the tubular member 4, and may be ring-shaped or clip-shaped.

[0030] Furthermore, the tubular member 4 and the inner wall of the cylinder 14 are spaced apart by at least a predetermined distance (for example, a distance at which the tubular member 4, which has been plastically deformed by substantially uniform compression when it collides with the stopper member 23, will not come into contact with the inner wall of the cylinder 14) so ​​that the tubular member 4 does not come into contact with the inner wall of the cylinder 14. As a result, even if the tubular member 4 collides with the stopper member 23 and is plastically deformed, it deforms without being hindered by the inner wall of the cylinder 14, and the impact on the piston member 10 is sufficiently absorbed.

[0031] The hole 10c is formed along the central axis from the lower end of the main body 10a to partway along the rod-shaped portion 10b, thereby making the piston member 10 lighter than if the hole 10c were not formed.

[0032] The female thread portion 10d is formed from the tip of the rod-shaped portion 10b to partway along the central axis. The male thread portion 50b of the bolt member 50, which will be described later, can be screwed into the female thread portion 10d.

[0033] A seal member 11 such as an O-ring is provided in the circumferential direction in the groove portion 10e.

[0034] A generally cylindrical stopper member 23 is provided at the top of the cylinder 14 so as to surround a portion of the rod-shaped portion 10b of the piston member 10. That is, the rod-shaped portion 10b is disposed in a state of being inserted through a hole 13 in the stopper member 23. The cylinder 14 is also provided with through-holes 14a for releasing air within the space 6 to the outside during operation. Although only two through-holes 14a are provided in FIGS. 1 and 2, a plurality of through-holes 14a may be provided in the circumferential direction.

[0035] The stopper member 23 restricts the movement of the tubular member 4 within the cylinder 14, and has a groove 23a provided along the outer periphery and a groove 23b provided along the inner periphery. The groove 23a is used to fix the other end of the cylinder 14 by crimping to the stopper member 23. Furthermore, a seal member 12 such as an O-ring is provided in the circumferential direction in the groove 23b.

[0036] The material of the cylinder 14 may be selected and the thickness of the outer periphery may be appropriately adjusted so that the cylinder 14 can undergo radial plastic deformation in the event that the piston member 10 of the actuator 1 becomes immobile for some reason, or in the event that the initial combustion volume of the actuator 1 is reduced and the explosive burns, generating a combustion pressure exceeding the pressure resistance value of the cylinder 14 (in the event of an abnormality). Examples of materials that can be used for the cylinder 14 include metals such as iron, aluminum, brass, and copper, and alloys such as stainless steel. As a result, in the event of the abnormality, the cylinder 14 undergoes radial plastic deformation, which reduces (relaxes) the sealing performance of the sealing member 12, such as an O-ring, and creates a gap between the sealing member 12 and the inner wall of the cylinder 14 through which generated gas can pass. Therefore, by allowing gas generated in the event of the abnormality to leak out from this gap, the gas is released from through-hole 14a to the outside of cylinder 14, passes through the gap between the outer wall of cylinder 14 and the inner wall of bottomed tubular portion 19, passes into container 18, and causes sealing portion 40 (sealing material) described below to break due to the gas pressure, and is released from hole 24 to the outside of container 18, thereby preventing rupture of cylinder 14 (fail-safe function). Note that when this fail-safe function is provided, a space (gap) is provided between the outer wall of cylinder 14 and the inner wall of bottomed tubular portion 19 that allows cylinder 14 to undergo sufficient plastic deformation in the radial direction.

[0037] The gas generator 17 is arranged below a main body portion 10a (described later) of the piston member 10 in a state where it is press-fitted into the lower open end of the cylinder 14. In addition, a cylindrical member 3 is provided around the cup body 17a of the gas generator 17 to form a predetermined distance between it and the piston member 10.

[0038] The push-up member 15 is made of metal (aluminum, iron, or the like, and may also be an alloy), resin, or a composite material of resin and metal, CFRP, fiber-reinforced resin, or the like, and as shown in FIG. 1, has a bottomed tubular portion 19 arranged to cover a part of the cylinder 14, that is, the outer part of the cylinder 14 excluding the vicinity of the open end on the side where the gas generator 17 is arranged, and a disk-shaped support portion 20 provided as a flange (brim-shaped portion) at the opening of the bottomed tubular portion 19 and supporting the projectile 16.

[0039] The bottomed tubular portion 19 has a bottom 19a that is generally plate-shaped or generally columnar (in this embodiment, generally columnar), a hole 51 formed on the lid portion 21 side of the bottom 19a, a hole 52 (second hole) that has a smaller diameter than hole 51, and a hole 53 (first hole) that communicates with hole 51 via hole 52 and has a larger diameter than hole 52. Hole 51 has a larger diameter than the diameter of the head portion 50a of the bolt member 50. Hole 52 has a smaller diameter than the diameter of the head portion 50a, and can guide the male thread portion 50b of the bolt member 50 inserted from the hole 51 side toward the hole 53 side. The hole portion 53 has approximately the same shape as one end (upper end) of the rod-shaped portion 10b, and becomes a fitting portion into which one end of the rod-shaped portion 10b fits by inserting one end of the rod-shaped portion 10b through an insertion opening 53a provided on the cylinder 14 side of the bottom 19a of the bottomed tubular portion 19.

[0040] The bolt member 50 has its male threaded portion 50b inserted into hole 52 from the hole 51 side and threadedly engaged with the female threaded portion 10d of the rod-shaped portion 10b fitted in hole 53, thereby connecting the rod-shaped portion 10b and the push-up member 15. At this time, one end of the rod-shaped portion 10b is non-circular and is fitted into hole 53 of approximately the same shape, so that the rod-shaped portion 10b does not rotate together when the bolt member 50 is threaded into the female threaded portion 10d. Specifically, because the tip ends of the push-up member 15 and the piston member 10 are non-circular and fit together, when the bolt member 50 is fastened together, the push-up member 15 can be rotated while being fixed, and the piston member 10 tightens toward the gas generator 17, allowing for tightening without co-rotating.

[0041] In the initial state, the support part 20 is spaced apart from the inner bottom surface of the container 18. The support part 20 also has a hole 26 for facilitating the ejection of the projectile 16 by reducing the effect of negative pressure generated between the bottom of the projectile 16 and the support part 20 during operation. The outer periphery of the support part 20 is formed so as not to come into contact with the inside of the container 18. The upper surface of the support part 20 is also provided with at least one (eight in this embodiment) movement prevention member 27 for preventing the projectile 16 from moving in the circumferential direction of the bottomed tubular part 19.

[0042] The movement prevention members 27 are generally triangular members made of resin or a composite material such as resin and metal, CFRP, or fiber-reinforced resin, and a plurality of them are provided rotationally symmetrically around the bottomed tubular portion 19. Holes 26 are provided between each of the movement prevention members 27. Here, as a modified example, only one movement prevention member 27 may be provided. Even in this case, a plurality of holes 26 are provided in the support portion 20.

[0043] 1, the bottom of container 18 is provided with a plurality of holes 24 that connect the inside and outside of container 18, holes 25 into which base 2 is inserted, and bolt fastening holes 29. Also, as shown in FIG. 1, the bottom of container 18 has a recess in the center, and this center and the periphery of the center form a staircase shape with at least two steps.

[0044] A sealing member 40 (sealing material) is attached to each of the multiple holes 24 on the container 18 side. This sealing material, which is, for example, a tape-like material, breaks due to the negative pressure generated between the support member 20 and the bottom of the container 18 during activation. When the push-up member 15 moves rapidly within the container 18, negative pressure is generated in the area between the push-up member 15 and the bottom surface of the container 18. This makes it difficult to move the push-up member 15. Therefore, by providing the holes 24, the negative pressure phenomenon can be reduced, allowing the push-up member 15 to move smoothly. However, before activation, the sealing member 40 (sealing material) is provided to prevent liquid, dust, etc. from entering the container 18 and to prevent deterioration or damage to the projectile 16.

[0045] Hole 25 is closed by fastening hole 2a provided in flange 2B of base 2 located outside the bottom of container 18 from the inside of container 18 with bolt 28 through hole 29. Also, by reducing the distance between support 20 and the bottom surface of the inside of container 18, projectile 16 is prevented from falling to the bottom surface of the inside of container 18.

[0046] As shown in FIG. 3, a portion of the open end of the container 18 is formed with a notch 18a and three fitting portions 18b, each of which is smaller in depth than the notch 18a. The fitting portions 18b are portions that can fit into an inner portion (not shown) of the lid portion 21, allowing the lid portion 21 to be attached to the opening of the container 18. The other end 70b of the bridle line 70 shown in FIG. 6, which will be described later, can be disposed in the notch 18a. Specifically, the other end 70b of the bridle line 70 can protrude from the inner side of the container 18 to the outer side of the container 18. The notch 18a may be disposed anywhere in the opening of the container 18, as long as it is not located at the fitting portion 18b. Furthermore, there is no particular problem even if multiple notches are provided, and multiple bridle lines corresponding to each notch may be disposed. Furthermore, one or more of the fitting portions 18b may have the same shape as the notch portion 18a.

[0047] The bridle line 70 is a string-like or rope-like annular member, and as shown in Figures 7 and 8 (one specific example of the flying object 30 shown in Figure 5, which will be described later), has one end 70a that can be connected to one end of a suspension line 73 of the projectile 16, and the other end 70b that can be connected to one end of a linear connector 80 for the flying object on the flying object 30, which will be described later. The bridle line 70 and the suspension line 73 constitute what is known as a line used for a projectile 16 such as a parachute, and this line may further include a so-called center line, etc., as necessary.

[0048] As shown in FIG. 4, the aircraft linear connector 80 includes a linear member 81 and an annular member 83. As described below, one end is directly connected to the bridle line 70 (for example, by tying or by forming a loop structure on the bridle line 70 and directly connecting thereto), and the other end is directly connected to a portion of the aircraft 30 (for example, by tying). It is preferable to use multiple aircraft linear connectors 80 to facilitate balancing the aircraft 30 after the projectile 16 is deployed. For example, when four aircraft linear connectors 80 are used, as shown in FIGS. 7 and 8, the aircraft 30 can be more easily balanced after the projectile 16 is deployed. FIG. 7 shows a state during operation when four aircraft linear connectors 80 are attached to the other end 70b of the bridle line 70, and FIG. 8 shows a state after operation, as shown in FIG. 7.

[0049] Linear member 81 has, at one end, a loop structure 82 and a taut stitched portion 84 formed by passing a tip end thereof through the inside of annular member 83 and folding it back, and taut stitching the tip end to a midpoint of linear member 81. The inner periphery of loop structure 82 is sized to allow passage of another loop structure (loop structure 88, described below) that is temporarily formed by folding back a midpoint of linear member 81. Furthermore, it is preferable that the surface of linear member 81 near at least the portion that comes into contact with annular member 83 be relatively non-slip (for example, by adding a resin containing rubber or silicone to at least a portion of the portion that comes into contact with annular member 83).

[0050] The linear member 81 has another end portion at which a connecting portion 85 is formed that can be directly connected to the bridle line 70 connected to the injection product 16. This connecting portion 85 has a loop structure formed by forming a tacking portion 86 by tacking the tip of the other end portion of the linear member 81 to an intermediate portion of the linear member 81. Here, the connecting portion 85 may have any shape and may be connected by any connection method as long as it can directly connect to the bridle line 70. The connecting portion 85 may also be connected directly to the suspension line 73 of the injection product 16 without using the bridle line 70. The connecting portion 85 may also be in any form as long as it can be directly connected to the bridle line 70 or the suspension line 73.

[0051] Furthermore, a hook-and-loop fastener 87 with a hook surface is provided in the linear member 81 midway between the taut stitched portion 84 and the taut stitched portion 86. This hook-and-loop fastener 87 is detachable from a hook-and-loop fastener 93 provided on a pocket 90, which will be described later.

[0052] The outer peripheral portion of the annular member 83 is formed to be of a size that can pass through the inner peripheral portion of the aforementioned another loop structure (loop structure 88 to be described later). Further, the outer shape of the annular member 83 has at least a part of an annular portion through which the tip of the linear member 81 can pass inside, and by the method of tying the linear connector 80 for a flying object to be described later, the aforementioned another loop structure (loop structure 88 to be described later) can be hooked and tied to an object (in this embodiment, the arm 34 of the flying object 30) for connection. It may be of any shape such as circular, elliptical, polygonal, etc. Also, the annular member 83 may be made of any material such as metal, alloy, resin, leather, etc., as long as its shape does not easily change or collapse even when a predetermined force (for example, the force applied when pulling the linear member 81 on one end side of the linear member 81 to be described later) is applied.

[0053] Incidentally, when the distance from the geometric center of the annular member 83 to the closest outer peripheral portion is R, and the length when the loop structure 82 is stretched the most by the annular member 83 is L, it is preferable that the relationship L < R holds. Thereby, after hooking the aforementioned another loop structure (loop structure 88 to be described later) and tying it to an object (in this embodiment, the arm 34 of the flying object 30) for connection by the method of tying the linear connector 80 for a flying object to be described later, it becomes difficult for the aforementioned another loop structure (loop structure 88 to be described later) to come off from the annular member 83, so it becomes difficult for one end portion of the linear member 81 to come loose. Here, as a specific example, for instance, as shown in FIG. 4, when the annular member 83 is a circular ring, the relationship W < L < R is applied. When the distance (outer diameter) from the geometric center (center of the outer circle) of the annular member 83 to the closest outer peripheral portion is R, and the length when the loop structure 82 is stretched the most by the annular member 83 is L, it is preferable that the relationship L < R holds.

[0054] Furthermore, when the width of the linear member 81 is W, it is preferable that the relationship W < L < R holds. Thereby, in addition to the effects when the above-mentioned relationship L < R holds, it becomes easier to pass through another loop structure (loop structure 88 described later) formed using a part of the linear member 81 in the inner peripheral portion of the loop structure 82 provided with the annular member 83.

[0055] As shown in FIG. 9(a), the pocket 90 includes a main body portion 91 made of a resin sheet, a leather sheet, a cloth-like body, etc., a hook surface fastener 92 provided on the left half of the main body portion 91, and a loop surface fastener 93 provided on the right half of the main body portion 91. When the main body portion 91 is folded in half in the direction of the white arrow in FIG. 9(a) to be in the folded state as shown in FIG. 9(b), the fasteners 92 and 93 are stored inside the main body portion 91. Also, either the surface on the side opposite to the side where the fastener 92 of the left half of the main body portion 91 in FIG. 9(a) is provided or the back surface of the right half of the main body portion 91 in FIG. 9(a) can be attached to the outer wall of the storage container 18 and the body 31 with double-sided tape or an adhesive as shown in FIG. 6. The fastener 93 is not only detachable from the fastener 92 but also detachable from the fastener 87 provided on the linear member 81.

[0056] Next, a method of tying the linear connector 80 for the flying object to the arm 34 of the flying object 30 will be described while referring to FIGS. 10 to 12. Note that the order of the following steps of the tying method may be interchanged.

[0057] First, as shown in FIG. 10(a), wind around the vicinity of the stitching portion 84 of the linear member 81 once from the lower part of the arm 34 to obtain the state shown in FIG. 10(b).

[0058] Next, as shown in FIG. 11(a), the linear member 81 is wound one more time around the taut stitched portion 84. At this time, as shown in FIG. 11(a), the excess length of the taut stitched portion 84 of the linear member 81 is prevented from becoming too long. Also, as shown in FIG. 11(a), the wound linear members 81 are made to cross each other (the state of portion 89). Next, as shown in FIG. 11(a), the annular member 83 is moved toward the tip end of the loop structure 82, the inner periphery of the loop structure 82 is widened, and a part of the linear member 81 is used to temporarily form a loop structure 88 that is not a closed structure.

[0059] Next, as shown in FIG. 11(b), the loop structure 88 is passed through the inner periphery of the loop structure 82. Subsequently, as shown in FIG. 12(a), the loop structure 88 is folded back, and the inner periphery of the loop structure 88 is passed through the annular member 83 so that the annular member 83 passes through the inner periphery of the loop structure 88. Thereafter, as shown in FIG. 12(b), the tip of the loop structure 88 is moved to the position of the loop structure 82. Then, the linear member 81 is pulled toward one end of the linear member 81 (the end connected to the bridle line 70) in the direction of the arrow shown in FIG. 12(b) and tightly fastened so that there is no slack, resulting in the state shown in FIG. 12(c) (a state in which one end of the aircraft linear connector 80 is tied and connected). Note that if the annular member 83 is one that does not easily change shape or does not easily lose its shape even when force is applied, it is possible to prevent the loop structure 88 from slipping off the annular member 83. Furthermore, even if at least a portion of the surface of the linear member 81 near the portion that comes into contact with the annular member 83 is relatively non-slip, the loop structure 88 can be prevented from slipping off and becoming detached from the annular member 83.

[0060] Next, in the pocket 90 shown in Fig. 6, the pocket 90 is opened (see Fig. 9(a)), and then the hook-and-loop fastener 87 is attached to the hook-and-loop fastener 93 at a position where there is no slack in the linear member 81. Next, the main body 91 of the pocket 90 is folded in half so that the surfaces of the hook-and-loop fasteners 92 and 93 face each other, and the hook-and-loop fasteners 92 and 93 are attached, and the pocket 90 is closed (see Fig. 9(b)).

[0061] If there are multiple aircraft linear connectors 80, the above steps are carried out for all of the aircraft linear connectors 80, and each is fastened to the corresponding arm 34.

[0062] The projectile 16 is contained within the container 18 between the inner surface of the container 18 and the outer surface of the bottomed tubular portion 19 of the push-up member 15, for example, so as to surround the outer surface of the bottomed tubular portion 19. The projectile 16 is folded so that its outer surface does not come into contact with the inside of the container 18. The projectile 16 is connected to one end 70a of the bridle line 70 via a suspension line 73. Here, as a modified example, the projectile 16 may be folded with its outer surface in contact with the inside of the container 18.

[0063] The gas generator 17 may use only an igniter, or may be a gas generator equipped with an igniter and a gas generant. Also, a hybrid or stored-type gas generator may be used, in which a gunpowder-type igniter ruptures the seal of a small gas cylinder, releasing the gas inside. In this case, the pressurized gas in the gas cylinder may be a non-flammable gas such as argon, helium, nitrogen, or carbon dioxide, or a mixture of these. Furthermore, the gas generator may be equipped with a heating element made of a gas generant composition, a thermite composition, or the like, to reliably propel the piston when the pressurized gas is released.

[0064] The piston member 10, the cylinder 14, the push-up member 15, the gas generator 17, and the like mainly constitute an ejection section that ejects the projectile 16.

[0065] Furthermore, as shown in the schematic diagram of the aircraft in Figure 5, the safety device 100 is connected and fixed to the airframe 31 of the aircraft 30 by bolts (not shown) from the airframe 31 side through fixing holes (not shown) in the base 2. At this time, as shown in Figure 5, the base 2 connects the container 18 to the airframe 31 in a position that does not block the holes 24. Therefore, the aircraft 30 includes the airframe 31, the safety device 100 connected to the airframe 31, one or more propulsion mechanisms (e.g., propellers) 32 connected to the airframe 31 and propelling the airframe 31, and a plurality of legs 33 provided on the bottom of the airframe 31.

[0066] Furthermore, because the flange portion 2B of the base 2 is provided outside the bottom of the container 18, the base 2 can be directly attached to the airframe 31 of the aircraft 30. As a result, the airframe 31 is subjected to the recoil during activation directly, rather than through the container 18. However, since the impact of activation on the container 18 can be reduced, the strength of the bottom of the container 18 can be reduced compared to when the base 2 is provided inside the container 18. In other words, the strength of the bottom of the container 18 can be safely reduced compared to conventional containers (for example, by designing the bottom of the container 18 to be reduced to a safe, predetermined thickness), thereby ensuring the same level of safety as conventional containers, while making the container 18 lighter overall than conventional containers. Furthermore, because the bottom of the container 18 has a step, the strength of the bottom of the container 18 can be increased compared to a flat bottom without a step.

[0067] The safety device 100 also includes an abnormality detection device 200 (not shown in FIG. 5) that includes an acceleration sensor and the like that detects abnormalities in the flying object 30.

[0068] Here, we will explain the functional configuration of the abnormality detection device 200. As shown in Fig. 13, the abnormality detection device 200 includes a sensor (detection unit) 210 and a control unit (a computer having a CPU, ROM, RAM, etc.) 220, and is electrically connected to an igniter in the gas generator 17 of the ejection unit, a memory unit 201, a flight control unit 202, and a notification unit 203.

[0069] The sensor 210 detects the flight status (including collisions, crashes, etc.) of the flying object 30. Specifically, the sensor 210 is a sensor selected from one or more of an acceleration sensor, a gyro sensor, a barometric pressure sensor, a laser sensor, an infrared sensor, a monocular / compound vision sensor, an ultrasonic sensor, a voltmeter, a fuel gauge, etc., and can acquire data on the flight status of the flying object 30, such as the speed, acceleration, angular acceleration, inclination, altitude, position, and obstacles that may hinder the flight of the flying object 30, data on the surrounding environment (obstacles, topography, shape of buildings, etc.), data on the amount of power supply, amount of fuel, etc.

[0070] The control unit 220 has, as its functional configuration, an abnormality detection unit 221, a calculation unit 222, and a notification unit 223. The abnormality detection unit 221, the calculation unit 222, and the notification unit 223 are functionally realized by the control unit 220 executing a predetermined program.

[0071] The anomaly detection unit 221 not only detects abnormal conditions related to the surrounding environment based on information received from the sensor 210, but also detects the flight status of the aircraft 30 (whether an abnormal condition such as a fall has occurred during flight). In other words, the anomaly detection unit 221 detects whether the sensor 210 and the aircraft 30 are operating normally. For example, the anomaly detection unit 221 can detect an emergency situation for personnel inside the aircraft 30, a fatal malfunction of equipment inside the aircraft 30, the aircraft 30's power supply being below a predetermined value, the aircraft 30's fuel amount being below a predetermined value, the aircraft 30's acceleration or angular velocity being above or below a predetermined value, the aircraft 30's attitude angle being above a predetermined value, and the aircraft 30's descent speed being above a predetermined value. Furthermore, when the aircraft 30 is being operated by an operator using a controller, the anomaly detection unit 221 can detect the loss of an operation signal from the controller or the reception of an abnormal signal. Furthermore, the anomaly detection unit 221 can detect the loss of a signal from the controller or the reception of an abnormal signal from a ground station.

[0072] The calculation unit 222 determines whether the flight status of the flying object 30 is abnormal based on each piece of data actually measured and acquired by the sensor 210. Specifically, the calculation unit 222 determines whether there is an abnormality by comparing each piece of data acquired by the sensor 210 with each preset threshold value. The calculation unit 222 also receives obstacle detection signals, distance detection signals, altitude detection signals, etc. from the sensor 210 in real time, and determines whether there is an abnormality based on each of these received signals. The calculation unit 222 also determines whether the flying object 30 is approaching or entering a prohibited area, or deviating from the planned route, based on the position information of the flying object 30.

[0073] Furthermore, when the calculation unit 222 determines that the flight state of the flying object 30 is abnormal, it outputs an abnormality signal (which may include a command signal to start or operate other equipment) to the outside. Note that an abnormality signal output unit may be provided separately from the calculation unit 222, and configured so that this abnormality signal output unit outputs an abnormality signal in response to a command from the calculation unit 222.

[0074] When the abnormality detection unit 221 detects an abnormality in the sensor 210 and the flying object 30, the notification unit 223 notifies a manager or the like that an abnormality has been detected.

[0075] The storage unit 201 can store various data such as data acquired by the sensor 210 and determination data when an abnormality is determined by the calculation unit 222.

[0076] The flight control unit 202 controls the flight attitude of the aircraft 30, and is capable of stopping the propulsion device (motor, etc.) provided in the aircraft 30 if an abnormality is determined by the calculation unit 222.

[0077] The notification unit 203 is capable of notifying the surroundings of an abnormality when an abnormality is determined by the calculation unit 222. For example, the notification unit 203 activates a sound generating device (such as an alarm) and / or a lighting device (such as an LED) to notify the surroundings of the abnormality.

[0078] In the above-described configuration, when an abnormality signal is received from the calculation unit 222 and the gas generator 17 is activated when, for example, an aircraft 30 on which the safety device 100 is mounted falls, the pressure of the gas generated by the activation propels the piston member 10 upward within the cylinder 14 from the initial state shown in Figures 1, 5, and 6. This causes the push-up member 15, which has a bottomed tubular portion 19 connected to the rod-shaped portion 10b of the piston member 10, to propel (project) upward within the container 18. As a result, as shown in Figure 7, the lid portion 21 is removed, the open end of the container 18 is released, and the projectile 16 is ejected from the container 18 outward (upward in the plane of the paper in Figures 1 and 2). At this time, the suspension line 73 and bridle line 70 connected to the ejected projectile 16 are also ejected along with the projectile 16, and the aircraft linear connector 80 is pulled via the connecting portion 85 connected to the bridle line 70, causing the pocket 90 to deploy and the linear member 81 to be released to the outside. Negative pressure is also generated in the region between the support portion 20 of the push-up member 15 and the bottom surface of the container 18, causing the sealing portion 40 (sealing material) to rupture (see FIG. 2), and outside air flows into the container 18 from the outside of the hole 24. Subsequently, from the state shown in FIG. 2, the piston member 10 and the tubular member 4 move upward, but the tubular member 4 collides with the stopper member 23 and stops. Then, as shown in FIG. 8, if the projectile 16 is a parachute or paraglider, the projectile 16 deploys after being ejected from the container 18. Furthermore, as shown in Figure 8, when tension (tensile force) is applied to the suspension line 73 and the bridle line 70, tension (tensile force) is also applied to the linear member 81. Here, Figures 7 and 8 show an example of four aircraft linear connectors 80 being deployed (the pockets 90 corresponding to the four aircraft linear connectors 80 are not shown). This allows the aircraft 30 to be stably suspended from the deployed parachute.

[0079] According to this embodiment, it is possible to provide a linear connector 80 for an aircraft that can be connected to a projectile 16 (deployed object) such as a parachute or paraglider without using a connector such as a carabiner, a safety device 100 that launches a projectile 16 (deployed object) such as a parachute or paraglider to which the linear connector 80 for an aircraft is connected, and an aircraft 30 equipped with the safety device 100.

[0080] Furthermore, the aircraft linear connector 80, which is fastened to an arm provided on the aircraft 30, can also be provided separately from the safety device 100, making it easier to attach the safety device 100 to the aircraft 30. Furthermore, the aircraft linear connector 80 can be installed on the aircraft 30 in advance so that the state of the aircraft linear connector 80 when activated allows the aircraft 30 to be suspended in a balanced manner, making it easier to adjust the aircraft linear connector 80.

[0081] Furthermore, by using a fastening method using the annular member 83, one end of the aircraft linear connector 80 can be firmly fastened to the arm 34 of the aircraft 30. Note that the location where one end of the aircraft linear connector 80 is fastened is not limited to the arm 34, and the aircraft linear connector 80 may be fastened to any location on the aircraft 30 as long as a fastening location is provided.

[0082] Furthermore, the above configuration is provided with a hole 24 that connects the inside and outside of the container 18, and a sealing part 40 (sealing material) that seals the hole 24 in the initial state and breaks due to negative pressure generated during operation in the region between the support part 20 of the push-up member 15 and the bottom surface of the container 18. Therefore, according to this embodiment, even during operation, it is possible to prevent a decrease in injection performance that occurs when the container 18 does not have a hole 24. Furthermore, according to this embodiment, since the hole 24 is sealed by the sealing part 40 (sealing material) in the initial state, it is possible to prevent early deterioration or damage to the injection product 16 before operation.

[0083] Although the embodiments of the present invention have been described above with reference to the drawings, the specific configuration is not limited to these embodiments. The scope of the present invention is defined by the claims rather than the description of the above embodiments, and further includes all modifications within the meaning and scope of the claims.

[0084] In the above embodiment, the linear member 81 is held using the pocket 90 having the hook-and-loop fasteners 92 and 93, but this is not limited to this. For example, instead of the pocket 90, a loop-type hook-and-loop fastener may be directly attached to a predetermined position on the container 18, and the hook-and-loop fastener 87 may be attached to hold the linear member 81.

[0085] Furthermore, the safety device 100 of the above embodiment is not limited to the one shown in the above embodiment as long as it has a configuration that can eject a projectile. For example, the safety device may have an ejection section that ejects a projectile into the container, and a section on the container that is similar to the notch, and the safety device may have a lid that does not close the opening of the container.

[0086] Furthermore, in the above embodiment, a portion of the base 2 was configured to be located outside the container 18, but the entire base 2 may also be configured to be located inside the container 18.

[0087] Furthermore, while the above embodiments employ a gas generator as a power source, the configuration is not limited as long as it is capable of applying a driving force to the sliding member to propel the sliding member through the cylinder. For example, a drive source such as an elastic body type using an elastic body such as a spring, a gas cylinder type using gas pressure trapped in a container, or a chemical reaction type (non-explosive) in which two or more substances are mixed and reacted to generate gas pressure may be employed. Furthermore, instead of the ejection devices of the above embodiments and modifications, a retractable (also called a pulling) ejection device may be used. Examples of such retractable ejection devices include a system in which a rocket is launched and a parachute is extracted, a system in which a weight is launched by an actuator and then a parachute is extracted, a system in which a projectile is launched by an actuator and then a parachute is extracted, and a system in which a pilot chute is first launched and then a parachute is extracted by the pilot chute.

[0088] Here, we will explain examples of the above-mentioned pull-out type launching device, including a system in which a rocket is launched and the parachute is pulled out, a system in which a weight is launched with an actuator and then the parachute is pulled out, a system in which a projectile is launched with an actuator and then the parachute is pulled out, and a system in which a pilot chute is first launched and then the pilot chute is pulled out. Note that parts with the same last two digits as those in the above embodiment are the same as those explained in the above embodiment unless otherwise specified, and so explanations will be omitted.

[0089] (280: A retractable launcher that launches a rocket and pulls out a parachute) As shown in FIG. 14, launch device 280, which is provided on airframe 231 outside safety device 290, includes storage section 281 that stores rocket 282 in an initial state (see FIG. 14(a)), rocket 282 connected to a parachute (not shown) in container 211 of safety device 290 via line 283 (see FIG. 14(b)), and a flight control section (not shown) similar to flight control section 202. Rocket 282 has an explosive or chemical reaction (non-explosive) propulsion section (not shown) at its bottom, and is activated when it receives a launch command signal from the flight control section in the event of an emergency, causing it to launch upward as shown in FIG. 14(b). This allows rocket 282 to be launched in the event of an emergency, and the parachute in container 211 to be pulled out of container 211 and then deployed.

[0090] (The actuator launches a weight and then the parachute is pulled out using the pull-out launcher 380) As shown in FIG. 15 , the launching device 380, mounted on the airframe 331 outside the safety device 300, includes a storage section 381 that stores the weight 382 in an initial state (see FIG. 15( a) ), the weight 382 connected to a parachute (not shown) in the container 311 of the safety device 300 via a line 383 (see FIG. 15( b) ), an actuator 384, and a flight control section (not shown) similar to the flight control section 202. The actuator 384 may be the same as the launching device of the above embodiment, or may be an elastic type using an elastic body such as a spring, a gas cylinder type using gas pressure trapped in a container, or a chemical reaction type (non-explosive) that generates gas pressure by mixing two or more substances and causing a chemical reaction. When the actuator 384 receives a launch command signal from the flight control section in the event of an abnormality, it is activated and can launch the weight 382 upward, as shown in FIG. 15( b) . As a result, in the event of an abnormality, weight 382 can be thrown, the parachute inside container 311 can be pulled out to the outside of container 311, and then the parachute can be deployed.

[0091] (An actuator launches the projectile and then pulls out the parachute.) 16, safety device 400 includes parachutes 456 and 457, a cup-shaped container 451 that contains parachutes 456 and 457 before deployment, a support column 452 provided on the inner bottom of container 451, three tube sections 453, 454, and 455 that have actuators 421, 422, and 423 inside and are connected to support column 452, and a flight control section (not shown) similar to flight control section 202. Actuator 421 is provided inside tube section 453, actuator 422 is provided inside tube section 454, and actuator 423 is provided inside tube section 455. Tube sections 453, 454, and 455 are arranged to face in different directions, for example, like the ribs of an umbrella.

[0092] Projectile 453a is inserted into tube 453 with a portion of it exposed, and similarly, projectile 454a is inserted into tube 454 with a portion of it exposed, and projectile 455a is inserted into tube 455 with a portion of it exposed. Parachute 456 is connected to projectile 453a by string 458 and to projectile 455a by string 459. Parachute 457 is connected to projectile 455a by string 460 and to projectile 454a by string 461. When actuator 384 receives a launch command signal from the flight control unit in the event of an abnormality, it is driven to launch projectiles 453a, 454a, and 455a in the directions of the arrows in FIG. 16 in the event of an abnormality.

[0093] The above-mentioned actuators 421, 422, 423, support column 452, tube portions 453, 454, 455, projectiles 453a, 454a, 455a, etc. mainly constitute the injection device of this modified example.

[0094] 16 in the event of an emergency, parachutes 456 and 457 inside container 451 can be pulled out of container 451, and then parachutes 456 and 457 can be deployed. Note that only one of parachutes 456 and 457 may be provided.

[0095] (A pull-out type ejection device that pulls out the parachute using a pilot chute) Instead of the weight 382 of the above-mentioned ejection device 380 (FIG. 15), a pilot chute (not shown) may be connected to the line 383, and in the event of an abnormality, the pilot chute may be ejected and deployed first, and the parachute (not shown) in the container 211 may be pulled out and then deployed.

[0096] Furthermore, in the above embodiment, the container 18 is formed in a cylindrical shape, but is not limited to this, and may be formed in other shapes, such as a rectangular tube.

[0097] Furthermore, in the above-described embodiments, when a parachute or a paraglider is used as the projectile, the parachute or the paraglider may be packed in a manner that breaks or peels off when activated.

[0098] Furthermore, while the above embodiments have exemplified a parachute or a paraglider as the projectile, the projectile may also include a lift-generating member. Examples of lift-generating members include a parafoil, a Rogallo parachute, a single-surface parachute, an airplane wing, a propeller, and a balloon. Furthermore, if the lift-generating member has a control line, the safety device preferably includes a steering mechanism that can use the control line to change the inclination angle of the launched lift-generating member. This steering mechanism may include, for example, multiple reels that reel in the control lines connected to the lift-generating member, and a motor that powers these reels. The motor can be driven to reel in or release the control lines, thereby tensioning or loosening the lift-generating member as needed.

[0099] Alternatively, the flying object may be equipped with a safety device that can launch a net instead of a parachute or paraglider. This allows the flying object to be hooked onto a hook or protrusion by timing the launch of the net toward the hook or protrusion. As a result, the flying object can be prevented from falling and crashing to the ground. Alternatively, medicines, luggage, etc. may be launched instead of a parachute or paraglider.

[0100] The flying object may also be equipped with a safety device that can launch a deflated or folded float together with a drive mechanism (such as an inflation device including a gas generator) by an actuator, and then inflate and deploy the float using the drive mechanism. This can prevent the flying object from sinking and can serve as a marker for a recovery location in the event that the flying object crashes.

[0101] The aircraft may also be equipped with a safety device that can launch a deflated or folded float and parachute together with a drive mechanism (such as an inflation device including a gas generator) by an actuator, and deploy the float and parachute by the drive mechanism. This reduces the falling speed of the aircraft when it crashes, prevents the aircraft from sinking, and can serve as a marker for the recovery location when the aircraft crashes.

[0102] Alternatively, the parachute may be launched together with a drive mechanism (such as a cutting device with a drive unit) by an actuator, and after the parachute has deployed, some of the connecting members connecting the parachute to the aircraft may be cut by the drive mechanism, shifting the center of gravity of the aircraft body and causing it to fall sideways, and then the aircraft may be equipped with a safety device that can mitigate the impact of impact with the ground or the like using an airbag device provided on the side of the aircraft that is falling.

[0103] Alternatively, the flying object may be equipped with a safety device that uses an actuator to launch a so-called paramotor together with a drive mechanism (including a drive unit such as a power source), and after the parachute or paraglider is fully deployed, the drive mechanism can drive the motor to rotate the propeller. This prevents the parachute or paraglider from becoming entangled in the propeller. A paramotor is a device that is capable of flying by obtaining thrust from a power source (such as a motor-driven propeller rotation device) attached to the harness of the parachute or paraglider.

[0104] In addition, the aircraft may be equipped with a safety device that can launch a sound generating device together with a drive mechanism (including a drive unit such as a power supply) using an actuator, and activate the sound generating device using the drive mechanism when the aircraft crashes, thereby alerting those around it to danger.

[0105] In addition, the aircraft may be equipped with a safety device that uses an actuator to launch a lighting device (such as a flashlight) together with a drive mechanism (including a drive unit such as a power source), and that activates the lighting device via the drive mechanism when the aircraft crashes, thereby alerting those around it to danger.

[0106] In addition, the aircraft may be equipped with a safety device that can launch a fire extinguisher together with a drive mechanism (including a drive unit such as a power source) using an actuator, and activate the fire extinguisher using the drive mechanism when the aircraft crashes, thereby spraying a fire extinguishing agent onto the aircraft body and surrounding area.

[0107] The flying vehicle may also be equipped with a safety device that uses an actuator to launch a pre-launched payload (such as an expensive device) with a parachute together with a drive mechanism, and deploys the parachute of the payload with a parachute using the drive mechanism, thereby providing focused protection for the payload with a parachute.

[0108] The flying vehicle may also be equipped with a safety device that uses an actuator to eject a previously ejectable payload (such as an expensive device) equipped with an airbag device together with a drive mechanism (such as an inflation device including a gas generator), and then inflates and deploys the airbag of the payload with the airbag device using the drive mechanism. This allows for focused protection of the payload with the airbag device.

[0109] The aircraft may also be equipped with a safety device that can launch a distress signal transmitter together with a drive mechanism (including a drive unit such as a power source) by an actuator, and activate the distress signal transmitter by the drive mechanism when the aircraft crashes, thereby enabling the location of the crash to be identified.

[0110] The flying vehicle may also be equipped with a safety device that uses an actuator to launch a black box with a parachute (such as a flight recorder) together with a drive mechanism (such as an inflation device including a gas generator), and that uses the drive mechanism to deploy the parachute of the black box with a parachute when the flying vehicle crashes. This allows for the primary protection of the black box with a parachute, and as a result, flight data can be protected. [Explanation of symbols]

[0111] 1, 384, 421, 422, 423 Actuators 2 bases 2A Cylindrical member 2B flange 2a, 10c, 22c, 24, 25, 26, 51, 52, 53 holes 2c Insertion port 3 Cylindrical member 4 Tubular members 5. Retaining member 6 Space 10 Piston member 10a, 91 Main body 10b Rod-shaped part 10d female thread 10e, 23a, 23b groove 11, 12 Sealing member 13 Hole 14 cylinders 14a Through hole 15 Push-up member 16 Projectile 17 Gas Generator 17a Cup Body 17b Electrode 18 container 18a Notch 18b Mating part 19 Bottomed cylindrical part 19a bottom 20 Support part 21 Lid 22 Connectors 22a Main body 23 Stopper member 27 Anti-movement member 28 volts 29 holes 30 Flying Objects 31 aircraft 33 Legs 34 Arm 40 Sealing part 50 bolted components 50a head 50b male thread 53a Insertion opening 60 Closure member 70 Bridle Line 70a (of a bridle line) one end 70b (other end of bridle line) 73 Suspension Line 80 Linear connector for aircraft 81 Linear members 82, 88 Loop structure 83 Annular member 84, 86 Backstitch 85 Connecting part 87, 92 (hook surface) hook and loop fasteners 93 (loop surface) hook-and-loop fastener 89 (Linear member) part 90 pockets 100, 290, 300, 400 safety equipment 200 Anomaly Detection Device 201 Storage section 202 Flight Control Unit 203 Information Department 210 Sensors 220 Control Unit 221 Abnormality detection unit 222 Arithmetic section 223 Notification Department 281, 381 storage area 282 Rocket 382 Weight 452 Support column pipe section 453, 454, 455, pipe section 453a, 454a, 455a projectiles 458, 459, 460, 461 String

Claims

1. A linear connector for an aircraft, one end of which can be fastened and connected to a part of the aircraft equipped with a safety device, and the other end of which can be directly connected to a deployable body included in the safety device or a line connected to the deployable body, an annular member; a linear member having a loop structure at one end formed by passing a tip end portion through the inside of the annular member and folding it back, and fixing the tip end portion to an intermediate portion thereof, and having a connecting portion formed at the other end that can be directly connected to the deployable body or a line connected to the deployable body; Equipped with an inner periphery of the loop structure is formed to a size that allows passage of another loop structure that is temporarily formed by folding back the linear member at a midpoint between one end and the other end of the linear member; A linear connector for an aircraft, characterized in that the outer periphery of the annular member is formed to a size that allows it to pass through the inner periphery of the other loop structure.

2. The linear connector for an aircraft described in claim 1, characterized in that when R is the distance from the geometric center of the annular member to the closest outer peripheral portion and L is the length of the loop structure when it is most extended by the annular member, the relationship L < R holds.

3. 3. The linear connector for an aircraft according to claim 2, wherein when the width of the linear member is W, the relationship W<L<R holds.

4. an injection unit that injects an object; the ejection unit and a container containing the ejection unit; a line connected at one end to the projectile; Equipped with A safety device characterized in that the other end of the line is directly connected to the other end of the linear connector for an aircraft described in any one of claims 1 to 3.

5. Further comprising an abnormality detection device capable of detecting abnormalities in the aircraft or the surrounding environment; 5. The safety device according to claim 4, wherein the abnormality detection device activates the ejection unit when the abnormality is detected.

6. 6. The safety device according to claim 5, further comprising a flight control unit that stops a propulsion device provided on the flying object when the abnormality is detected by the abnormality detection device.

7. The aircraft and The safety device according to any one of claims 4 to 6, which is provided on the aircraft body; and one or more propulsion mechanisms coupled to the airframe for propelling the airframe.

8. A fastening method for fastening one end of the linear connector for an aircraft according to any one of claims 1 to 3, the other end of which can be connected to an end of a line connected to a deployable body, to a part of the aircraft, a step of winding the one end of the linear connector for the aircraft around a portion of the aircraft; a step of folding back the aircraft linear connector at a midpoint between the other end and the one end to temporarily form another loop structure; a step of passing the other loop structure through an inner periphery of the loop structure; Folding the another loop structure back and passing the inner periphery of the another loop structure through the annular member so that the annular member passes through the inner periphery of the another loop structure; a step of moving the tip of the other loop structure to the position of the loop structure, and then pulling the linear member toward the other end of the aircraft linear connector, tightening it, and tying it; A fastening method comprising:

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