Safety device and flying vehicle equipped with safety device

Abstract

To provide a safety device which can normally inject an injection object such as a parachute by reducing friction between the surface of the injection object such as the parachute and an inner wall surface of a storage container compared to before, and to provide a flight body provided with the safety device.SOLUTION: A safety device includes an actuator 1, a push-up member 15 which is pushed up into one direction by the actuator 1, an injection object 16 which is pushed up while being supported by a support part 20 of the push-up member 15 and a storage container 18 which stores the push-up member 15 and the injection object 16 onto an inner part. On an inner wall part of a peripheral wall part 18a of the storage container 18, a plurality of protruded parts 18a1 and a plurality of recessed parts (groove parts) 18a2 are provided. The protruded parts 18a1 are provided so as to run along a sliding direction of a piston member of which the longitudinal direction is connected with the push-up member 15. Further, cross-section shapes of the protruded parts 18a1 are formed in wavy shapes containing semi-circles.SELECTED DRAWING: Figure 2

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, Patent Document 1 discloses an example of the above-mentioned parachute safety device, which includes a container (receptacle) with an opening, a parachute, a plug for dividing the internal space of the container into a combustion chamber and a storage chamber for storing the parachute, and at least one pyrotechnic gas generator. [Prior art documents] [Patent documents]

[0005] [Patent Document 1] European Patent No. 3050805 Summary of the Invention [Problem to be solved by the invention]

[0006] In a device such as that described in Patent Document 1, the surface of the parachute is in contact with the inner wall surface of the container (receptacle), and friction (sliding resistance) occurs between the surface of the parachute and the inner wall surface of the container (receptacle) when the parachute is released. Therefore, due to this friction (sliding resistance), the parachute may not be released properly or the release power of the parachute may be weakened.

[0007] Therefore, the present invention aims to provide a safety device that reduces the friction (sliding resistance) between the surface of a projectile such as a parachute and the inner wall surface of a container more than conventional devices, thereby enabling the projectile such as a parachute to be launched normally, and an aircraft equipped with such a safety device. [Means for solving the problem]

[0008] (1) The present invention provides a sliding mechanism including a sliding member, an actuator having a power source that generates a driving force to slide the sliding member to one side, a bottomed tubular portion that is connected to the one side of the sliding member and an inside of a bottom portion and that slides along the sliding member when the sliding member slides; The aforementioned Outer periphery of bottomed cylindrical part In the initial state, 、 projectile A folded parachute or paraglider that is a support part that supports the sliding member, the actuator, the support part, and the projectile; and a container that contains at least the sliding member, the actuator, the support part, and the projectile, an outer periphery of the support portion is formed so as not to come into contact with an inner wall portion of the container from the initial state to after activation, A plurality of linear protrusions formed along the sliding direction of the sliding member are arranged side by side in the circumferential direction on the inner wall of the container. 、 Multiple The aforementioned By providing the protrusions, recesses are provided between the protrusions, and the tips of the protrusions are A convex or flat shape, The projectile together with the outer peripheral portion of the bottomed cylindrical portion The recess supports the injection object, and a space is formed between the injection object and at least a portion including the bottom of the recess.

[0009] (2) In the safety device of (1) above, when the convex portion includes a corner, it is preferable that the corner is rounded.

[0010] (3) In the safety device of (1) above, the convex portion is an elongated linear portion having a triangular, rectangular, trapezoidal, or semicircular cross section. Any single type of shape or a combination of multiple types It is preferable that:

[0011] (4) In the safety device described in (1) above, a vehicle body, the safety device according to claim 1 provided on the vehicle body, and one or more propulsion mechanisms coupled to the vehicle body and propelling the vehicle body. flying object 、 Alternatively, it is preferable that the apparatus further comprises an abnormality detection device capable of detecting an abnormality in the surrounding environment, and that the abnormality detection device activates the actuator when the abnormality is detected.

[0012] (5) In the safety device of (4) above, it is preferable to further include a flight control unit that stops a propulsion device provided in the aircraft when the abnormality detection device detects the abnormality.

[0013] (6) The present invention provides a device comprising: a sliding member; an actuator having a power source that generates a driving force for sliding the sliding member in one direction; a bottomed tubular part that connects the one side of the sliding member with the inside of a bottom and slides along with the sliding member when the sliding member slides; a support part that is provided on the outer periphery of the bottomed tubular part and supports a pilot chute that is a projectile in an initial state; and a container that contains at least the sliding member, the actuator, the support part, and the projectile inside. Another container; and a parachute contained in the another container. Equipped with The pilot chute is connected to the hand parachute or paragliding connected to the outer periphery of the support part is formed so as not to come into contact with the inner wall part of the container from the initial state to after activation, the inner wall part of the container has a plurality of linear convex parts formed along the sliding direction of the sliding member and arranged in parallel in the circumferential direction, and the provision of the plurality of convex parts provides concave parts between the convex parts, the tip part of each of the convex parts has a convex shape or a flat shape and supports the projectile together with the outer periphery part of the bottomed tubular part, and a space is formed between the projectile and at least a part including the bottom of the concave part. .

[0015] ( 7 The aircraft according to the present invention comprises a fuselage and the above-mentioned (1) to ( 6 ) and one or more propulsion mechanisms coupled to the vehicle for propelling the vehicle. [Effects of the Invention]

[0016] According to the present invention, it is possible to provide a safety device that can normally launch a projectile such as a parachute by reducing the friction (sliding resistance) between the surface of the projectile, such as a parachute, and the inner wall surface of the container more than before, and an aircraft equipped with the safety device. [Brief explanation of the drawings]

[0017] [Figure 1]1 is a cross-sectional view showing an initial state of a safety device according to a first embodiment of the present invention. [Figure 2] 2 is a plan view showing the safety device of FIG. 1 with a cover removed. FIG. [Figure 3] 1. FIG. 4 is a diagram showing a modified example of the uneven portion on the inner wall surface of the container used in the safety device of FIG. [Figure 4] FIG. 2 is a schematic diagram showing the flying body to which the safety device (initial state) of FIG. 1 is attached. [Figure 5] FIG. 2 is a block diagram showing the functional configuration of the safety device of FIG. 1. [Figure 6] FIG. 6 is a cross-sectional view showing an initial state of a safety device according to a second embodiment of the present invention. [Figure 7] 7 is a plan view showing the safety device of FIG. 6 with the lid and the parachute removed. FIG. DETAILED DESCRIPTION OF THE INVENTION

[0018] First Embodiment A safety device and an aircraft according to a first embodiment of the present invention will be described below with reference to FIGS.

[0019] 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.

[0020] 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".

[0021] 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 FIG. 1) 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.

[0022] 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.

[0023] 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.

[0024] 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).

[0025] 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.

[0026] 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.

[0027] 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.

[0028] As shown in Fig. 1, tubular member 4 is held by holding member 5 at the bottom of rod-shaped portion 10b with one end in contact with main body portion 10a. Tubular member 4 is made of a material that undergoes plastic deformation and has a lower tensile strength than piston member 10 and 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.). Here, holding member 5 may be an elastic member such as rubber, or may be made of the same material as tubular member 4, and may be ring-shaped or clip-shaped.

[0029] 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.

[0030] 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.

[0031] 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.

[0032] A seal member 11 such as an O-ring is provided in the circumferential direction in the groove portion 10e.

[0033] A substantially 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 FIG. 1, a plurality of through-holes 14a may be provided in the circumferential direction.

[0034] 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.

[0035] 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.

[0036] 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.

[0037] 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.

[0038] 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.

[0039] 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.

[0040] 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.

[0041] 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.

[0042] As shown in FIGS. 1 and 2, the container 18 has a peripheral wall 18a and a bottom 18b. As shown in FIG. 2, the peripheral wall 18a has an inner wall with a plurality of protrusions 18a1 that support the projectile 16 and a plurality of recesses (grooves) 18a2 that provide spaces between the projectile 16. The protrusions 18a1 are linear, with their longitudinal direction aligned with the sliding direction of the piston member 10. The cross section of the protrusions 18a1 is formed in a wavy shape that includes a semicircle. The container 18 is preferably made of polyamide (natural) or polyamide (carbon glass FRP). Both polyamide (natural) and polyamide (carbon glass FRP) have a static friction coefficient of 0.71 and a dynamic friction coefficient of 0.08.

[0043] The recesses (grooves) 18a2 are formed between adjacent protrusions 18a1 along the sliding direction of the piston member 10, and may be formed by grinding the peripheral wall 18a (at which time the protrusions 18a1 are also formed at the same time), or by adhering two protrusions 18a1 to the peripheral wall 18a so that they are adjacent to each other with a predetermined distance between them. It is sufficient that one or more recesses (grooves) 18a2 are provided on the inner wall of the peripheral wall 18a. Furthermore, the width of the opening of the recesses (grooves) 18a2 (the distance between the apexes of adjacent protrusions 18a1) is preferably 1 mm to 3 mm so that the projectile 16 does not come into contact with the bottom of the recesses (grooves) 18a2. As a result, the projectile 16 can be supported by the convex portions 18a1, and the contact area between the projectile 16 and the inner wall surface of the peripheral wall portion 18a can be reduced (for example, to 50% or less) compared to a conventional case in which only the inner wall surface of the peripheral wall portion is a curved surface without convex and concave portions and concave portions (grooves) 18a2. Furthermore, to ensure that the projectile 16 does not come into contact with the bottom of the concave portions (grooves) 18a2, it is preferable that the depth of the concave portions (grooves) 18a2 is 1 mm or more (for example, within a range of 1 mm to 3 mm).

[0044] Here, modified examples of the convex portion 18a1 and the concave portion (groove portion) 18a2 will be described with reference to FIG. 3, but the modified examples of the convex portion 18a1 and the concave portion (groove portion) 18a2 are not limited to those shown in FIG. 3. For example, the concave portion (groove portion) may have any shape as long as the width of the concave portion (groove portion) is sufficient to support the injection material at the opening (between the convex portions) of the concave portion (groove portion). The left-hand side views of each of FIGS. 3(a) to 3(h) show a portion of the components when the convex portion and the concave portion (groove portion) are bonded to the inside of the container (illustration is omitted from the middle of the left-right direction of the page). The right-hand side views of each of FIGS. 3(a) to 3(h) show a portion of the inside of the container when the convex portion and the concave portion (groove portion) are formed by grinding (illustration is omitted from the middle of the left-right direction of the page. Parts in the thickness direction of the container are also omitted). The modified example shown in FIG. 3 can also be applied to the second embodiment and other modified examples described below.

[0045] The cross-sectional shape of the convex portion of the modified example shown in FIG. 3 may be a trapezoid (including a substantially trapezoid as shown in FIGS. 3(a) and 3(b)), a triangle (preferably with an apex angle of 60° to 120° (preferably 90°), including a substantially triangular shape as shown in FIGS. 3(c) and 3(d) but not necessarily an isosceles triangle), a square (including a substantially square shape as shown in FIGS. 3(e) and 3(f)), or a semicircular shape (including a substantially semicircular shape as shown in FIGS. 3(g) and 3(h)). As shown in FIGS. 3(a) to 3(f), the corners of each convex portion are preferably rounded (processed to form a rounded shape known as R). This prevents the projectile 16 from getting caught on the corners. The convex portions and the concave portions (grooves) may be formed using a single shape from among the shapes shown in FIG. 3, or a combination of multiple shapes may be used to form the convex portions and the concave portions (grooves). The convex portions in this embodiment and the modified examples may be formed continuously, or may be formed intermittently as long as the contact area between the projectile 16 and the inner wall surface of the peripheral wall portion 18a does not increase.

[0046] The recesses (grooves) are formed between the protrusions shown in FIG. 3, and the bottoms may be acute-angled (see FIGS. 3(b) and (d)), flat (see FIGS. 3(f) and (h)), or curved (see FIGS. 3(a), (c), (e), and (g)).

[0047] 1, bottom 18b 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, bottom 18b 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.

[0048] 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.

[0049] 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.

[0050] 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 with its outer surface in contact with the inner wall surface of the peripheral wall portion 18a of the container 18. The projectile 16 is connected via a suspension line (not shown) to one end of a bridle line (not shown) attached to the airframe 31 of the flying vehicle 30 (described below) or the container 18. Here, as a modified example, the projectile 16 may be folded in an accordion-like shape (having a wave-shaped cross section) from the edge toward the center, or may be folded in some other way.

[0051] Here, in this embodiment, the projectile 16 is, for example, a parachute or paraglider. The base fabric of the parachute or paraglider is preferably formed by knitting at least one fiber selected from the group consisting of polyamide, polyester, polyimide, vinyl chloride, polycarbonate, acrylic, and polyolefin fibers. For example, the base fabric may be formed by joining together multiple pieces of fabric formed by knitting one type of fiber, or by joining together a fabric formed by knitting one type of fiber with a fabric formed by knitting another type of fiber, or by knitting together multiple types of fibers. Furthermore, the base fabric of the parachute or paraglider may be formed by at least one film selected from films made of polyamide, polyester, polyimide, vinyl chloride, polycarbonate, acrylic, or polyolefin resins. For example, the base fabric may be formed by joining together multiple pieces of one type of film, or by joining together multiple types of films. The fabrics or films may be joined together by any means, such as pressure bonding, adhesion with an adhesive, or sewing.

[0052] Examples of polyamide fibers or resins include nylon 6, nylon 6,6, and nylon 4,6. Examples of polyester fibers or resins include polyethylene terephthalate, polybutylene terephthalate, polyethylene naphthalate, and polybutylene succinate. Examples of polyimide fibers or resins include aromatic polyimides and aliphatic polyimides. Examples of vinyl chloride fibers or resins include vinyl chloride films, examples of polycarbonate fibers or resins include polycarbonate films, examples of acrylic fibers or resins include acrylic films, and examples of polyolefin fibers or resins include low-density polyethylene, high-density polyethylene, and polypropylene. The base fabric may be coated with a coating agent such as silicone or polyurethane.

[0053] 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.

[0054] 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.

[0055] 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.

[0056] 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.

[0057] 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.

[0058] Here, we will explain the functional configuration of the abnormality detection device 200. As shown in Fig. 4, 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.

[0059] 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.

[0060] 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.

[0061] 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.

[0062] 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.

[0063] 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.

[0064] 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.

[0065] 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.

[0066] 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.

[0067] 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.

[0068] In the above configuration, when an aircraft 30 or the like equipped with the safety device 100 falls, an abnormality signal is received from the calculation unit 222 and the gas generator 17 is activated. The gas pressure generated by the activation propels the piston member 10 upward within the cylinder 14 from the initial state shown in FIG. 1 . This propels (projects) the push-up member 15, which has a bottomed tubular portion 19 connected to the rod-shaped portion 10b of the piston member 10, upward within the container 18. This causes the lid portion 21 to come off, opening the open end of the container 18 and ejecting the projectile 16 outward (upward in the plane of FIG. 1 ) from within the container 18. 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, allowing outside air to flow into the container 18 from the outside of the hole 24. Subsequently, 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, if the projectile 16 is a parachute or a paraglider, the projectile 16 is ejected from the container 18 and then deployed.

[0069] According to this embodiment, the formation of the convex portions 18a1 and the concave portions 18a2 reduces the contact area between the surface of the projectile 16, such as a parachute, and the inner wall surface of the peripheral wall portion 18a of the container 18 compared to the case of a conventional flat inner wall surface. This reduces the friction (sliding resistance) between the parachute surface and the inner wall surface of the container compared to the conventional case. As a result, it is possible to provide a safety device 100 and an aircraft 30 equipped with the safety device 100 that can properly launch a projectile, such as a parachute, without the projectile getting caught on the inner wall surface.

[0070] Furthermore, since the friction (sliding resistance) between the surface of the projectile 16 such as a parachute and the inner wall surface of the peripheral wall portion 18a of the container 18 can be reduced more than before, it is possible to reduce the amount of explosive charge in the igniter (not shown) in the gas generator 17 of the actuator 1. As a result, it is possible to reduce the size of the gas generator 17, and therefore the size and weight of the actuator 1. In other words, the weight of the safety device 100 can be reduced.

[0071] Furthermore, the friction (sliding resistance) between the surface of the projectile 16, such as a parachute, and the inner wall surface of the peripheral wall 18a of the container 18 can be reduced more than before, thereby increasing the projectile 16's launch speed more than before. Therefore, if the projectile 16 is a parachute or paraglider, the time until the parachute opens can be shortened, making it possible to reduce the altitude loss of the installation target (for example, the flying vehicle 30).

[0072] 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.

[0073] Second Embodiment Next, a safety device for an aircraft according to a second embodiment of the present invention will be described with reference to Figures 6 and 7. In this embodiment, reference numerals having the same last two digits as those in the first embodiment are similar, and therefore their explanations may be omitted. Furthermore, parts that are not particularly described are similar to the safety device and aircraft according to the first embodiment, and therefore their explanations may be omitted.

[0074] The safety device 300 in this embodiment differs from the first embodiment mainly in that (1) the cross section of the container 118 is formed to have a shape that approximates a circle with a chord in one portion (a circle with a portion cut out) (see Figure 7), (2) the shape of the support portion 120 and the lid portion 121 of the push-up member 115 are shaped to imitate the cross section shape of the container 118 (see Figure 7), (3) the installation position of the actuator 101 is offset from the geometric center of the cross section of the container 118 (see Figure 7), and (4) a plurality of convex portions 118a1 and a plurality of concave portions 118a2 are formed.

[0075] As described above, container 118 is formed so that its cross section approximates a circle with a chord in part, but the part including the chord of container 118 is a flat surface. Lid 121 is formed so that it can close the opening of container 118.

[0076] The protrusions 118a1 have a semicircular cross section and are provided so that their longitudinal direction is along the sliding direction of the piston member 110. The recesses 118a2 have their bottoms as the inner wall portion of the peripheral wall portion 118a and are formed between adjacent protrusions 118a1.

[0077] According to this embodiment, it is possible to achieve the same effects as those of the first embodiment.

[0078] 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. For example, the safety device only needs to have an ejection portion that ejects the projectile into the container, and the container may have any cross-sectional shape, such as a sector or a rectangle, and the lid may not close the opening of the container.

[0079] Furthermore, in each of the above embodiments, a portion of the base is configured to be located outside the container, but the entire base may also be configured to be located inside the container.

[0080] Furthermore, while a gas generator is used as the power source in each of the above embodiments, 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 used. Furthermore, instead of the ejection devices in the above embodiments and modifications, a draw-out type (also called a pulling type) ejection device may be used. Examples of such a draw-out type ejection device include a system in which a rocket is launched and a parachute is extracted, a system in which a weight is launched using an actuator and then a parachute is extracted, a system in which a projectile is launched using an actuator and then a parachute is extracted, and a system in which a pilot chute housed in a separate container is first launched by a launcher, and then the pilot chute is used to extract the parachute from the container of the present invention.

[0081] Furthermore, in each of the above 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.

[0082] Furthermore, while the above embodiments have described 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 projectile. 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 the reels. The motor can be driven to reel in or release the control lines, thereby tensioning or loosening the lift-generating member as needed.

[0083] 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.

[0084] 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.

[0085] 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.

[0086] 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.

[0087] 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.

[0088] 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.

[0089] 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.

[0090] In addition, the aircraft may be equipped with a safety device that can eject 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.

[0091] 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.

[0092] 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.

[0093] 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.

[0094] 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.

[0095] (Example) Next, safety device containers with the same configuration as the second embodiment were prepared according to Examples 1, 2, and Comparative Example 1, with the shapes of the convex and concave portions listed in Table 1 below. Tensile tests were conducted to verify that Examples 1 and 2 according to the present invention can reduce friction (sliding resistance) between the surface of a projectile, such as a parachute, and the inner wall surface of the peripheral wall of the container compared to the conventional method (Comparative Example). In these tensile tests, the piston member and the lifting member were attached to each container, and a projectile (in this test, a parachute made of a zero-porosity material) was housed in each container (assuming the initial state of the safety device). Three tests were conducted to determine the tensile force (N) required when the piston member was pulled up at a speed of 200 mm / min. The tensile force was measured using a Shimadzu Corporation precision universal testing machine, model AGX-20kNVD. The results of the tensile tests are also shown in Table 1 below. Before being placed in the container, the projectile was placed with the center of the deployed parachute on the top of a cylindrical member having the same shape as the cylinder 14 of the first embodiment, and then folded from the edge of the parachute toward the center in a bellows shape (with a wavy cross section). In this test, the parachute folded in this way was removed from the cylindrical member and placed in a test container, and the test was conducted.

[0096] [Table 1]

[0097] The results in Table 1 show that Examples 1 and 2 of the present invention can significantly reduce the friction (sliding resistance) between the surface of a projectile such as a parachute and the inner wall surface of the peripheral wall of the container compared to the conventional example (comparison example).

[0098] Furthermore, based on the results in Table 1, it can be seen that the projectile can be ejected smoothly if the friction (sliding resistance) between the surface of the projectile and the inner wall surface of the peripheral wall of the container is adjusted in advance so that the projectile can be ejected with an average tensile strength of 44 N or less. For example, even if a parachute, an example of a projectile, is made of a relatively flexible material, the parachute can be ejected smoothly if the friction (sliding resistance) between the surface of the folded parachute and the inner wall surface of the peripheral wall of the container is adjusted in advance (specifically, by changing the inner diameter of the container to match the flexibility of the parachute material) so that the projectile can be ejected with an average tensile strength of 44 N or less. [Explanation of symbols]

[0099] 1, 101 Actuator 2. 102 Foundations 2A, 102A cylindrical member 2B, 102B flange 2a, 102a hole 2c, 102c insertion port 3, 103 Cylindrical member 4, 104 Tubular members 5, 105 holding member 6, 106 space 10, 110 Piston member 10a, 110a Main body 10b, 110b Rod-shaped part 10c, 110c hole 10d, 110d female thread 10e, 110e groove 11, 12, 111, 112 sealing members 13, 113 hole 14, 114 cylinders 14a, 114a through hole 15, 115 Push-up member 16, 116 Projectile 17, 117 Gas generator 17a, 117a cup body 17b, 117b electrode 18, 118 container 18a, 118a Peripheral wall part 18a1, 118a1 convex part 18a2, 118a2 Recess (groove) 18b, 118b bottom 19, 119 Bottomed cylindrical part 19a, 119a bottom 20, 120 Support part 21, 121 Lid 22, 122 connectors 22a, 122a Main body 22c, 24, 25, 26, 51, 52, 53 holes 23, 123 Stopper member 23a, 23b, 123a, 123b Groove 27, 127 Anti-movement member 28, 128 volts 29, 129 holes 30 Flying Objects 31 aircraft 33 Legs 40 Sealing part 50 bolted components 50a head 50b male thread 53a Insertion opening 60 Closure member 100, 300 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

Claims

1. A sliding member; an actuator having a power source that generates a driving force to slide the sliding member to one side; a bottomed tubular portion that is connected to the one side of the sliding member and an inside of a bottom portion and that slides along the sliding member when the sliding member slides; a support portion provided on an outer periphery of the bottomed tubular portion, the support portion supporting a folded parachute or paraglider as the projectile in an initial state; a container that accommodates at least the sliding member, the actuator, the support, and the projectile therein; Equipped with an outer periphery of the support portion is formed so as not to come into contact with an inner wall portion of the container from the initial state to after activation, a plurality of linear convex portions formed along the sliding direction of the sliding member are arranged side by side in the circumferential direction on the inner wall portion of the container, and recesses are formed between the convex portions by providing the plurality of convex portions; each tip of the protrusion has a convex or flat shape and supports the injection object together with an outer peripheral portion of the bottomed tubular portion; A safety device characterized in that a space is formed between the projectile and at least a portion including a bottom of the recess.

2. 2. The safety device according to claim 1, wherein, when the convex portion includes corners, the corners are rounded.

3. 2. The safety device according to claim 1, wherein the convex portion has a shape selected from the group consisting of a triangular, rectangular, trapezoidal, and semicircular elongated linear portion, or a combination of two or more of these shapes.

4. A flying vehicle comprising an airframe, a safety device according to claim 1 provided on the airframe, and one or more propulsion mechanisms coupled to the airframe and propelling the airframe, or further comprising an abnormality detection device capable of detecting abnormalities in the surrounding environment, The safety device according to claim 1, wherein the abnormality detection device activates the actuator when the abnormality is detected.

5. 5. The safety device according to claim 4, 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.

6. A sliding member, an actuator having a power source that generates a driving force to slide the sliding member to one side; a bottomed tubular portion that is connected to the one side of the sliding member and an inside of a bottom portion and that slides along the sliding member when the sliding member slides; a support portion provided on an outer periphery of the bottomed cylindrical portion, the support portion supporting a pilot chute as a projectile in an initial state; a container that accommodates at least the sliding member, the actuator, the support, and the projectile therein; Another container, a parachute housed in the separate container; Equipped with the pilot chute is connected to the parachute or the paraglider via a connecting member; an outer periphery of the support portion is formed so as not to come into contact with an inner wall portion of the container from the initial state to after activation, a plurality of linear convex portions formed along the sliding direction of the sliding member are arranged side by side in the circumferential direction on the inner wall portion of the container, and recesses are formed between the convex portions by providing the plurality of convex portions; each tip of the protrusion has a convex or flat shape and supports the injection object together with an outer peripheral portion of the bottomed tubular portion; A safety device characterized in that a space is formed between the projectile and at least a portion including a bottom of the recess.

7. The aircraft and The safety device according to any one of claims 1 to 6, which is provided on the aircraft body; and one or more propulsion mechanisms coupled to the airframe for propelling the airframe.

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