Safety device and flying object provided with the same

Abstract

To provide a safety device capable of not only preventing reduction of injection performance but also preventing early deterioration or damaging of an object to be injected in an initial state at the time of actuation, and a flying object provided with the same.SOLUTION: This safety device comprises: an actuator; a pushing-up member pushed up in one direction by the actuator; an object to be injected, which is supported by a support of the pushing-up member and pushed up; and a bottomed cylindrical storage. The storage has a notch, and an other end 70b of a bridle line connected to a line connected to the object to be injected protrudes from the notch by a prescribed length. Fastening parts 70b1 and 70b2 are provided in parts of the other end 70b of the bridle line so as to prevent the other end 70b of the bridle line from entering the storage. At the time of actuation of the safety device, the fastening parts 70b1 and 70b2 are released.SELECTED DRAWING: Figure 6

Description

[Technical Field]

[0001] The present invention relates to a safety device for launching a projectile such as a parachute or a paraglider, and to an aircraft equipped with the safety device. [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 container for the safety device is fixed to the aircraft. In this case, it is preferable to have the other end of the line extend outside the container in advance to make it easier to attach the line to the aircraft. In this case, it is further desirable to maintain the length of the other end of the line extending outside the container at a predetermined length.

[0007] Therefore, an object of the present invention is to provide a safety device that can maintain the length of the other end of the line extending outside from the container at a predetermined length, and an aircraft equipped with such a safety device. [Means for solving the problem]

[0008] (1) A safety device according to the present invention comprises an ejection section that ejects a projectile, a container that contains the ejection section and the ejection section, and a line having one end connected to the ejection section, wherein the container has a bottomed tubular member with an open end formed at one end, and a notch formed in at least a part of the open end, and the line is arranged so that in an initial state, the other end of the line protrudes from inside the container to outside the container through the notch, and the other end of the line is provided with a protrusion that protrudes from inside the container to outside the container, and a fastener that is connected to the protrusion so as to be located inside the container in the initial state and prevents parts of the line other than the protrusion from protruding outside the container through the notch.

[0009] (2) In the safety device of (1) above, it is preferable that the fastening portion is formed by temporarily fastening at least a part of the other end of the line that protrudes from the inside of the container to the outside of the container by sewing or gluing, and that the temporary fastening is released when activated.

[0010] (3) In the safety device of (2) above, the fastening portion may be formed by bending at least a portion of the other end of the line that protrudes from inside the container to outside the container in a Z-shape.

[0011] (4) In the safety device of (1) above, the fastening portion may be a stopper member that is larger in width than the notch portion and that clamps the line.

[0012] (5) The aircraft of the present invention is characterized by comprising an airframe, any one of the safety devices (1) to (4) connected to the airframe, a propulsion mechanism connected to the airframe and propelling the airframe, and another line having one end connected to the other end of the line and the other end connected to the airframe. [Effects of the Invention]

[0013] According to the present invention, it is possible to provide a safety device that can maintain the length of the other end of the line extending outside from the container at a predetermined length, and an aircraft equipped with the safety device. [Brief explanation of the drawings]

[0014] [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 bridle line used in the safety device of FIG. 1, in which (a) is a diagram showing an initial state and (b) is a diagram showing a state in which the fastening portion is released from fastening. [Figure 5] FIG. 2 is a perspective view of the flying body to which the safety device (initial state) of FIG. 1 is attached. [Figure 6] FIG. 6 is an enlarged view of FIG. 5 with a portion omitted. [Figure 7] 6 is a perspective view showing a state in which the safety device of the flying object of FIG. 5 is in the middle of operation. FIG. [Figure 8] FIG. 6 is a partial cross-sectional view showing the state after the safety device of the flying object of FIG. 5 has been activated. DETAILED DESCRIPTION OF THE INVENTION

[0015] A safety device and an aircraft according to an embodiment of the present invention will be described below with reference to FIGS.

[0016] 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 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.

[0017] 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.

[0018] 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.

[0019] 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.

[0020] 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).

[0021] 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.

[0022] 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.

[0023] 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.

[0024] 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.

[0025] 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.

[0026] 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.

[0027] 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.

[0028] A seal member 11 such as an O-ring is provided in the circumferential direction in the groove portion 10e.

[0029] 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.

[0030] 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.

[0031] 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.

[0032] 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.

[0033] 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.

[0034] 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.

[0035] 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.

[0036] 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.

[0037] 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.

[0038] 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.

[0039] 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.

[0040] 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.

[0041] 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 bridle line 70 shown in FIG. 4 can be disposed in the notch 18a. Specifically, the protruding portion 70b3 at the other end of the bridle line 70 shown in FIG. 4 protrudes from the inner side of the container 18 toward the outer side of the container 18 (see FIG. 6), allowing the bridle line 70 to be hooked with the fastening portions 70b1 and 70b2 disposed inside the container 18. The notch 18a may be disposed anywhere in the opening of the container 18, as long as it is located at a position other than the fitting portions 18b. Furthermore, there is no particular problem even if there are multiple cutouts, and multiple bridle lines corresponding to the respective cutouts may be provided. Furthermore, one or more of the cutouts 18b may have the same shape as the cutouts 18a.

[0042] The bridle line 70 is a string-like or rope-like annular member having one end 70a connectable to one end of a suspension line 73 (see FIG. 8) of the projectile 16 and the other end 70b connectable to one end of a line 72 on the aircraft 30 side, which will be described later. The other end 70b is formed with the fastening portions 70b1 and 70b2 described above, and a protrusion 70b3 connected to the fastening portions 70b1 and 70b2 (see FIGS. 4 and 6). The bridle line 70 and the suspension line 73 constitute a so-called line used for a projectile 16 such as a parachute, and this line may further include a so-called center line, etc., as necessary.

[0043] Each of the fastening portions 70b1 and 70b2 is formed by forming a pair of Z-shaped bent portions at a portion of the other end portion 70b and temporarily fastening the portions by sewing (sewing) or by bonding with adhesive or welding, as shown in FIG. 4(a). The temporary fastening by sewing or bonding is releasable by the tensile force applied via the suspension line 73 upon activation, so that the fastening portions 70b1 and 70b2 change from their initial state to the release portions 70b11 and 70b21, as shown in FIG. 4(b). That is, when temporary fastening is performed by sewing, the strength of the stitching is set to a level that breaks upon activation. When temporary fastening is performed by bonding, the strength of the bonding is set to a level that peels off upon activation. By releasing the temporary fastening in this way (during deployment), the lines (attached to the parachute) and the aircraft 30 (specifically, the multiple arms 34 to which the lines 72 are attached), described below, receive uniform force and are balanced.

[0044] As shown in Figure 6, one end of a line 72 on the aircraft 30 side is connected to the other end 70b of the bridle line 70 via a carabiner 71. The line 72 splits into four lines midway, and the other ends of these four lines are connected to two pairs of opposing arms 34 of the eight arms 34 of the aircraft 30. These two pairs of opposing arms 34 are positioned perpendicular to each other (see Figure 7). As a modified example, a hook member such as a snap hook may be used instead of the carabiner 71, or the lines may be connected directly without using the carabiner 71 and hook member.

[0045] 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 also folded so that its outside does not come into contact with the inside of the container 18. The projectile 16 is connected, for example, to one end of a string (not shown), and the other end of the string is connected to the inside of the container 18 (for example, tied to the support portion 20 via a plurality of holes 26) or to the fuselage 31 of the flying object 30, which will be described later. Here, as a modified example, the projectile 16 may be folded with its outside in contact with the inside of the container 18.

[0046] 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.

[0047] 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.

[0048] As shown in Fig. 5, the safety device 100 is connected and fixed to the airframe 31 of the flying vehicle 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 Fig. 5, the base 2 connects the container 18 to the airframe 31 in a position that does not block the holes 24. Therefore, the flying vehicle 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.

[0049] 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.

[0050] In the above-described configuration, when the gas generator 17 is activated when, for example, an aircraft or the like 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 FIGS. 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 FIG. 7, the lid portion 21 is released, the open end of the container 18 is opened, and the projectile 16 is ejected outward (upward in the plane of the paper in FIGS. 1 and 2) from within the container 18. At this time, the suspension line 73 and the bridle line 70 connected to the ejected projectile 16 are also ejected together with the projectile 16. Furthermore, negative pressure is 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 ambient air flows into the container 18 from the outside of the hole 24. Subsequently, the piston member 10 and the tubular member 4 move upward from the state shown in FIG. 2, 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 is deployed after being launched from the container 18. Furthermore, as shown in FIG. 8, when tension (pulling force) is applied to the suspension line 73 and the bridle line 70, the temporary fastening of the fastening portions 70b1 and 70b2 is released. By releasing the temporary fastening in this way (during deployment), the lines (attached to the parachute) and the flying vehicle 30 (specifically, the multiple arms 34 to which the lines 72 are attached) receive uniform forces, resulting in balance.

[0051] According to this embodiment, it is possible to provide a safety device 100 that can maintain the length of the other end of the bridle line 70, which is connected to the suspension line 73 and extends outward from the cutout portion 18a of the container 18, at a predetermined length without increasing the number of parts. That is, with this safety device 100, the bridle line 70 can be installed regardless of the positions of the multiple arms 34 installed on the aircraft 30, making it easy to manufacture. Furthermore, according to this embodiment, the other end 70b of the bridle line 70 is hooked and fixed to the cutout portion 18a of the container 18, which improves the ease of handling of the line 72. Therefore, compared to when a line (attached to a parachute) is directly connected to the aircraft 31 through the inside of the container 18, the degree of freedom in the installation position of the safety device 100 can be improved.

[0052] Furthermore, the line 72 that connects to the arm provided on the flying vehicle 30 can also be provided separately from the safety device 100, making it easier to attach the safety device 100 to the flying vehicle 30. Furthermore, the line 72 can be installed on the flying vehicle 30 in advance so that the state of the line 72 when activated allows the flying vehicle 30 to be suspended in a balanced manner, making it easier to adjust the line 72.

[0053] Furthermore, since the bridle line 70 is annular, the strength of the bridle line 70 is increased without adding any other members, thereby reducing costs and weight.

[0054] 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.

[0055] 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.

[0056] In the above embodiment, each of the fastening portions 70b1, 70b2 is temporarily fastened by sewing or adhesive, but this is not limited to this. For example, each of the fastening portions 70b1, 70b2 may be a stopper member such as a clip or hairpin that clamps a portion of the other end of the bridle line 70, as long as it can set the length of the other end of the bridle line 70 that protrudes outward from the cutout portion 18a to a predetermined length. Note that this stopper member is larger than the width of the cutout portion and is large enough to prevent the bridle line 70 from protruding outward from the inside of the container through the cutout portion.

[0057] 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.

[0058] Furthermore, in the above embodiment, the bridle line 70 is annular, but this is not necessarily limited to this. For example, as long as the bridle line can be hooked onto the notch in the container by the fastener, the length of the other end of the bridle line that protrudes outside the container can be set to a predetermined length, and one end of the bridle line is connected to the other end of the suspension line 73, a single bridle line having only one fastener may be used.

[0059] 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.

[0060] Furthermore, in the above embodiment, a gas generator is used as the power source, but the configuration is not limited as long as it is possible to impart a driving force to the sliding member to propel the sliding member inside the cylinder. For example, an elastic body such as a spring, or a device using pressure from a gas cylinder may be used.

[0061] 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.

[0062] 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.

[0063] 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.

[0064] 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.

[0065] 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.

[0066] 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.

[0067] 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.

[0068] 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.

[0069] 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.

[0070] 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.

[0071] 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.

[0072] 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.

[0073] 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.

[0074] 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.

[0075] 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]

[0076] 1 actuator 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 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) 70b1, 70b2 Fastening part 70b3 Protrusion 70b11, 70b21 release part 71 Carabiner 72 lines 73 Suspension Line 100 safety equipment

Claims

1. an injection unit that injects an object; the ejection unit and a container containing the ejection unit; a line having one end connected to the injection portion; Equipped with The container has a bottomed tubular member with an open end formed at one end, A notch is formed in at least a part of the opening end, In an initial state, the line is arranged so that the other end of the line protrudes from the inside of the container to the outside of the container through the notch, A safety device characterized in that the other end of the line is provided with a protrusion that protrudes from inside the container to outside the container, and a fastening portion that is connected to the protrusion so as to be located inside the container in the initial state, and prevents any part of the line other than the protrusion from protruding outside the container through the cutout portion.

2. The fastening portion is formed by temporarily fastening by sewing or gluing at least a part of the other end of the line that protrudes from the inside of the container to the outside of the container, 2. The safety device of claim 1, wherein, upon activation, the temporary fastening is released.

3. The safety device according to claim 2, characterized in that the fastening portion is formed by bending at least a portion of the other end of the line that protrudes from inside the container to outside the container in a Z-shape.

4. 2. The safety device according to claim 1, wherein the fastening portion is a stopper member that is larger in width than the notch portion and that clamps the line.

5. The aircraft and a safety device according to any one of claims 1 to 4 coupled to the airframe; a propulsion mechanism coupled to the vehicle and configured to propel the vehicle; Another line having one end connected to the other end of the line and the other end connected to the aircraft; An aircraft characterized by comprising:

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