JP7796598B2 - Safety device and flying vehicle equipped with the safety device - Google Patents

Description

The present invention relates to a safety device for launching a projectile such as a parachute or paraglider, and to an aircraft equipped with such a safety device.

In recent years, advances in autonomous control technology and flight control technology have led to an accelerating industrial use of aircraft equipped with multiple rotors, known as drones. Drones fly by simultaneously rotating multiple rotors in a balanced manner, for example, and ascend and descend by increasing or decreasing the rotor speed, while moving forward and backward by tilting the aircraft through an increase or decrease in the rotor speed. It is expected that such aircraft will become more widespread worldwide in the future.

However, the risk of aircraft crashes like those mentioned above is considered dangerous and is hindering the widespread use of aircraft. To reduce the risk of such crashes, parachute devices for aircraft are being commercialized as safety devices.

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 interior space of the container into a combustion chamber and a storage chamber for storing the parachute, and at least one pyrotechnic gas generator.

European Patent No. 3050805

In devices such as that described in Patent Document 1, the surface of the parachute comes into contact with the inner wall surface of the container (receptacle), and when the parachute is released, friction (sliding resistance) occurs between the parachute surface and the inner wall surface of the container (receptacle). Therefore, during release, this friction (sliding resistance) can sometimes prevent the parachute from being released properly or weaken the power of the parachute's release.

The present invention aims to provide a safety device that reduces friction (sliding resistance) between the surface of a projectile such as a parachute and the inner wall surface of a container, thereby enabling the projectile to be launched normally, and an aircraft equipped with such a safety device.

(1) The present invention provides a device comprising: 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 part that connects the one side of the sliding member with the inside of its bottom and slides in tandem 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 folded parachute or paraglider 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, and the outer periphery of the support part is initially The sliding member is formed so as not to come into contact with the inner wall of the container from the initial state to after activation, and the inner wall of the container has a plurality of linear convex portions arranged in parallel in the circumferential direction along the sliding direction of the sliding member , and the provision of a plurality of the convex portions provides concave portions between the convex portions, and each tip of the convex portions has a convex or flat shape and supports the projectile together with the outer peripheral portion of the bottomed tubular portion , and a space is formed between the projectile and at least a part including the bottom of the concave portion.

(2) In the safety device described in (1) above, if the convex portion includes corners, it is preferable that the corners are rounded.

(3) In the safety device of (1) above, it is preferable that the convex portion has a shape of a single type or a combination of multiple types of elongated linear portions having a triangular, rectangular, trapezoidal, or semicircular cross section.

(4) The safety device of (1) above preferably further comprises an aircraft including an airframe, the safety device of claim 1 provided on the airframe, and one or more propulsion mechanisms coupled to the airframe and propelling the airframe , or an abnormality detection device capable of detecting an abnormality in the surrounding environment, and the abnormality detection device preferably activates the actuator when it detects the abnormality.

(5) It is preferable that the safety device of (4) above further includes a flight control unit that stops a propulsion device provided on the aircraft when the abnormality detection device detects the abnormality.

(6) The present invention provides a device comprising: 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 part that connects the one side of the sliding member to the inside of the 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; 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, wherein the pilot chute is connected to the parachute or parachute via a connecting member. The safety device may be connected to a glider , and 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, and the inner wall part of the container has a plurality of linear convex parts formed in parallel in the circumferential direction along the sliding direction of the sliding member, and the provision of a plurality of the convex parts provides concave parts between the convex parts, and each tip 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 .

( 7 ) The flying body according to the present invention is characterized by comprising an airframe, any one of the safety devices (1) to ( 6 ) provided on the airframe, and one or more propulsion mechanisms coupled to the airframe and propelling the airframe.

The present invention provides a safety device that reduces friction (sliding resistance) between the surface of a projectile such as a parachute and the inner wall surface of a container compared to conventional devices, allowing the projectile to be launched normally, as well as an aircraft equipped with such a safety device.

1 is a cross-sectional view showing an initial state of a safety device according to a first embodiment of the present invention. 2 is a plan view showing a state in which a cover portion is removed from the safety device of FIG. 1. [0023]FIG. 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. FIG. 2 is a schematic diagram showing the flying body to which the safety device (initial state) of FIG. 1 is attached. FIG. 2 is a block diagram showing the functional configuration of the safety device of FIG. 1 . FIG. 10 is a cross-sectional view showing an initial state of a safety device according to a second embodiment of the present invention. 7 is a plan view showing the safety device of FIG. 6 with the lid and parachute removed. FIG.

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. 1 to 5. FIG.

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 or dust. Examples of the blocking member 60 include any material that is waterproof and dustproof, such as an O-ring, hardened resin, or foam. Another variation of the blocking member 60 is a film-like wrapping that covers at least the edge of the lid 21 and the side of the container 18.

The parachute, which is an example of a deployable object that can be used in this embodiment, can be of various constructions, 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 the "RFD", "PARACOMMANDER", "PARAWING", "PARAFOIL", "SAILWING", "VOLPLANE" and "BALLUTE".

The actuator 1 comprises a piston member 10, which is a sliding member; a cylinder 14 that houses the piston member 10 and has a hole 13 through which the piston member 10 protrudes outward (upward in Figure 1) when actuated; a base 2 (squib holder) to which one end of the cylinder 14 is crimped and 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 that serves as a power source for moving the piston member 10 within the cylinder 14.

The base 2 includes a generally 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 side of the generally cylindrical member 2A opposite the cylinder 14 side.

The flange portion 2B is machined into a roughly U-shaped, horseshoe-like shape (not shown), and includes multiple holes 2a used for attachment to the container 18, multiple fixing holes (not shown) used for attachment to the airframe 31 of the aircraft 30 (described below), and an insertion opening 2c used for inserting the current-carrying 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 below) can be threaded into it. The inner wall of the fixing holes (not shown) is also internally threaded so that a bolt (not shown) can be threaded into the aircraft 30 (described below) from the airframe 31 side, thereby securing the base 2 to the aircraft 31.

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

Furthermore, the insertion port 2c of the base 2 and the connector 22 are configured to extend radially from the center of the base 2 when attached to the base 2, so that the wiring (not shown) can be arranged so as not to block the hole 24.

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

Although not shown, at least the upper end of the rod-shaped portion 10b has a non-circular cross section. 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. Furthermore, the tubular member 4 is fitted or loosely fitted to the lower part of the rod-shaped portion 10b, with one end in contact with the main body portion 10a. There may be a gap between the inner wall of the tubular member 4 and the outer wall of the rod-shaped portion 10b, but this gap should be small enough so as not to interfere with plastic deformation due to approximately uniform compression during a collision, as described below.

As shown in FIG. 1, the tubular member 4 is held by the retaining 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 retaining member 5 may be an elastic material such as rubber, or may be made of the same material as the tubular member 4, and may be ring-shaped or clip-shaped.

In addition, the tubular member 4 is separated from the inner wall of the cylinder 14 by a predetermined distance (for example, a distance at which the tubular member 4, plastically deformed by approximately uniform compression upon impact with the stopper member 23, does not come into contact with the inner wall of the cylinder 14) to prevent the tubular member 4 from coming into contact with the inner wall of the cylinder 14. As a result, even if the tubular member 4 is plastically deformed upon impact with the stopper member 23, it deforms without being hindered by the inner wall of the cylinder 14, adequately absorbing the impact on the piston member 10.

The hole 10c is formed along the central axis from the lower end of the main body 10a to halfway along the rod-shaped portion 10b. This makes the piston member 10 lighter than if the hole 10c were not formed.

The female threaded portion 10d is formed from the tip of the rod-shaped portion 10b to partway along the central axis. Furthermore, the male threaded portion 50b of the bolt member 50, described below, can be threaded into the female threaded portion 10d.

A sealing member 11, such as an O-ring, is provided circumferentially in the groove portion 10e.

A roughly cylindrical stopper member 23 is provided at the top of the cylinder 14, surrounding part of the rod-shaped portion 10b of the piston member 10. That is, the rod-shaped portion 10b is inserted into the hole 13 of the stopper member 23. The cylinder 14 also has through-holes 14a for releasing air from the space 6 to the outside during operation. Note that while only two through-holes 14a are shown in Figure 1, multiple through-holes 14a may be provided circumferentially.

The stopper member 23 restricts the movement of the tubular member 4 within the cylinder 14 and has a groove 23a along the outer periphery and a groove 23b along the inner periphery. The groove 23a is used to secure the other end of the cylinder 14 to the stopper member 23 by crimping. A sealing member 12, such as an O-ring, is provided circumferentially in the groove 23b.

The material of the cylinder 14 may be selected and the thickness of its outer periphery adjusted appropriately to allow 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 combustion pressure exceeding the pressure resistance value of the cylinder 14 (in an abnormal situation). Examples of materials that constitute 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 above-mentioned abnormal situation, the cylinder 14 undergoes radial plastic deformation, reducing (relaxing) the sealing performance of the sealing member 12, such as an O-ring, and creating 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 an abnormality to leak out through this gap, the gas is released from the cylinder 14 through the through-hole 14a to the outside of the cylinder 14, then passes through the gap between the outer wall of the cylinder 14 and the inner wall of the bottomed tubular portion 19 to the inside of the container 18, whereupon the gas pressure ruptures the sealing portion 40 (sealing material) described below, and the gas is released from the hole 24 to the outside of the container 18, thereby preventing rupture of the cylinder 14 (fail-safe function). Note that when this fail-safe function is provided, a space (gap) is provided between the outer wall of the cylinder 14 and the inner wall of the bottomed tubular portion 19 that allows the cylinder 14 to undergo sufficient plastic deformation in the radial direction.

The gas generator 17 is press-fitted into the lower open end of the cylinder 14 and is positioned below the main body portion 10a (described below) of the piston member 10. A cylindrical member 3 is provided around the cup body 17a of the gas generator 17 to create a predetermined distance between it and the piston member 10.

The push-up member 15 is made of metal (or an alloy of aluminum, iron, or the like), 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 part of the cylinder 14, i.e., the outer portion of the cylinder 14 excluding the vicinity of the open end on the side where the gas generator 17 is located, and a disk-shaped support portion 20 provided as a flange (brim-shaped portion) at the opening of the bottomed tubular portion 19 to support the projectile 16.

The bottomed tubular portion 19 has a bottom 19a that is generally flat or 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 is smaller in 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 diameter larger than the diameter of the head portion 50a of the bolt member 50. Hole 52 has a diameter smaller than the diameter of the head portion 50a, and can guide the male threaded portion 50b of the bolt member 50 inserted from the hole 51 side toward the hole 53 side. The hole 53 has approximately the same shape as one end (upper end) of the rod-shaped portion 10b, and serves as 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.

The bolt member 50 connects the rod-shaped portion 10b and the push-up member 15 by inserting the male threaded portion 50b into the hole 52 from the hole 51 side and threading it into the female threaded portion 10d of the rod-shaped portion 10b fitted into the hole 53. At this time, one end of the rod-shaped portion 10b is non-circular and fits into the hole 53, which has a substantially identical shape. Therefore, when the bolt member 50 is threaded into the female threaded portion 10d, the rod-shaped portion 10b does not rotate together. 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, the push-up member 15 can be rotated while being fixed, and the piston member 10 tightens toward the gas generator 17, allowing it to be tightened without rotating together.

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 that reduces the effect of negative pressure generated between the bottom of the projectile 16 and the support part 20 during operation, making it easier for the projectile 16 to be projected. 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 that prevents the projectile 16 from moving in the circumferential direction of the bottomed tubular part 19.

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 multiple members are provided rotationally symmetrically around the bottomed tubular portion 19. A hole 26 is provided between each of the movement prevention members 27. As a variant, only one movement prevention member 27 may be provided. Even in this case, multiple holes 26 are provided in the support portion 20.

As shown in Figures 1 and 2, the container 18 has a peripheral wall 18a and a bottom 18b. As shown in Figure 2, the peripheral wall 18a has an inner wall with multiple protrusions 18a1 that support the projectile 16 and multiple recesses (grooves) 18a2 that provide space between the projectile 16 and the protrusions 18a1. The protrusions 18a1 are linear, with their longitudinal direction aligned with the sliding direction of the piston member 10. The cross-sectional shape of the protrusions 18a1 is wavy and includes a semicircular shape. 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.

The recesses (grooves) 18a2 are formed between adjacent protrusions 18a1 along the sliding direction of the piston member 10. They may be formed by grinding the peripheral wall 18a (at which point the protrusions 18a1 are also formed), or by adhering two protrusions 18a1 to the peripheral wall 18a so that they are adjacent to each other and spaced a predetermined distance apart. It is sufficient for one or more recesses (grooves) 18a2 to be 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 vertices of adjacent protrusions 18a1) is preferably 1 mm to 3 mm to prevent the projectile 16 from contacting the bottom of the recesses (grooves) 18a2. This allows the projectile 16 to be supported by the convex portions 18a1, thereby reducing the contact area between the projectile 16 and the inner wall surface of the peripheral wall portion 18a (for example, by 50% or less) compared to a conventional case where there are no convex portions 18a1 or recesses (grooves) 18a2 and only the inner wall surface of the peripheral wall portion is a curved surface with no irregularities. Furthermore, to ensure that the projectile 16 does not come into contact with the bottom of the recesses (grooves) 18a2, it is preferable to make the depth of the recesses (grooves) 18a2 1 mm or more (for example, within the range of 1 mm to 3 mm).

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 opening (between the convex portions) of the concave portion (groove portion) is wide enough to support the projectile. The left-hand side of each of FIGS. 3(a) to 3(h) shows a portion of the components when the convex portion and the concave portion (groove portion) are bonded to the inside of the container (the illustration is omitted from the middle of the left-right direction of the page). The right-hand side of each of FIGS. 3(a) to 3(h) shows a portion of the inside of the container when the convex portion and the concave portion (groove portion) are formed by grinding (the illustration is omitted from the middle of the left-right direction of the page, and a portion of the container thickness direction is also omitted). The modified example shown in FIG. 3 can also be applied to the second embodiment and other modified examples described below.

The cross-sectional shape of the convex portion of the modified example shown in Figure 3 may be a trapezoid (including an approximate trapezoid as shown in Figures 3(a) and (b)), a triangle (preferably with an apex angle of 60° to 120° (preferably 90°), including an approximate triangle as shown in Figures 3(c) and (d). It does not necessarily have to be an isosceles triangle), a rectangle (including an approximate rectangle as shown in Figures 3(e) and (f)), or a semicircle (including an approximate semicircle as shown in Figures 3(g) and (h)). Furthermore, as shown in Figures 3(a) to (f), the corners of each convex portion are preferably rounded (processed to form a rounded shape known as an R). This prevents the projectile 16 from getting caught on the corners. Of the shapes shown in Figure 3, one type may be used alone, or multiple types may be combined to form the convex portions and concave portions (grooves). In this embodiment and the modified examples, the convex portions may be formed continuously, or may be formed intermittently as long as this does not increase the contact area between the projectile 16 and the inner wall surface of the peripheral wall portion 18a.

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

As shown in Figure 1, the bottom 18b of the container 18 has a plurality of holes 24 that connect the inside and outside of the container 18, a hole 25 into which the base 2 is inserted, and a hole 29 for bolt fastening. Also, as shown in Figure 1, the bottom 18b of the 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.

A sealing member 40 (sealing material) is attached to the container 18 side of each of the multiple holes 24. This sealing material, which is, for example, a tape-like material, breaks when negative pressure is 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 of the container 18, making 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, prior to activation, the sealing member 40 (sealing material) is provided to prevent liquids, dust, etc. from entering the container 18 and to prevent deterioration or damage to the projectile 16.

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

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 lifting 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 to the container 18. As a variation, the projectile 16 may be folded accordion-like (with a wavy cross section) from the edge toward the center, or may be folded in some other manner.

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 knitted from one type of fiber, or by joining together a piece of fabric knitted from one type of fiber with a piece of fabric knitted from another type of fiber, or by knitting together multiple types of fibers. Furthermore, the base fabric of the parachute or paraglider may be formed from at least one film selected from films made from polyamide, polyester, polyimide, vinyl chloride, polycarbonate, acrylic, or polyolefin resins. For example, the base fabric may be formed by joining together multiple pieces of film of the same type, or by joining together multiple types of film. The fabrics or films may be joined together by any means, such as crimping, bonding with an adhesive, or sewing.

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 film, polycarbonate fibers or resins include polycarbonate film, acrylic fibers or resins include acrylic film, and 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.

The gas generator 17 may be an igniter only, or a gas generator equipped with an igniter and gas generant. A hybrid or stored type gas generator may also be used, in which a gunpowder-type igniter ruptures the seal on a small gas cylinder, releasing the internal gas to the outside. 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. The gas generator may also be equipped with a heating element made of a gas generant composition or a thermite composition, etc., to reliably propel the piston when the pressurized gas is released.

The piston member 10, cylinder 14, push-up member 15, gas generator 17, etc. mainly constitute the ejection section that ejects the projectile 16.

Furthermore, as shown in the schematic diagram of the aircraft in Figure 5, the safety device 100 is connected and fixed to the aircraft body 31 of the aircraft 30 by bolts (not shown) from the aircraft body 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 aircraft body 31 in a position that does not block the holes 24. Therefore, the aircraft 30 comprises the aircraft body 31, the safety device 100 connected to the aircraft body 31, one or more propulsion mechanisms (e.g., propellers) 32 connected to the aircraft body 31 and propelling the aircraft body 31, and a plurality of legs 33 provided on the bottom of the aircraft body 31.

Furthermore, because the flange portion 2B of the base 2 is located 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 located inside the container 18. In other words, the strength of the bottom of the container 18 can be safely reduced compared to previous designs (for example, by designing the thickness of the bottom of the container 18 to be reduced to a safe, predetermined thickness), allowing the container 18 as a whole to be lighter than conventional designs while maintaining the same level of safety. 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.

The safety device 100 also includes an abnormality detection device 200 (not shown in Figure 5) that includes an acceleration sensor and other components that detect abnormalities in the flying object 30.

Here, the functional configuration of the abnormality detection device 200 will be explained. As shown in Figure 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 the igniter in the gas generator 17 of the ejection unit, a memory unit 201, a flight control unit 202, and an alarm unit 203.

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

The control unit 220 has the following functional components: an abnormality detection unit 221, a calculation unit 222, and a notification unit 223. The abnormality detection unit 221, calculation unit 222, and notification unit 223 are functionally realized by the control unit 220 executing a predetermined program.

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 involving 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 receipt of an abnormal signal. The anomaly detection unit 221 can also detect the loss of a signal from the ground station or the receipt of an abnormal signal.

The calculation unit 222 determines whether the flight status of the flying object 30 is abnormal based on the data acquired by the sensors 210 through actual measurements. Specifically, the calculation unit 222 determines whether an abnormality exists by comparing the data acquired by the sensors 210 with preset thresholds. The calculation unit 222 also receives obstacle detection signals, distance detection signals, altitude detection signals, etc. from the sensors 210 in real time, and determines whether an abnormality exists based on 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.

Furthermore, if the calculation unit 222 determines that the flight status 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 to output an abnormality signal in response to a command from the calculation unit 222.

When the abnormality detection unit 221 detects an abnormality in the sensor 210 or the flying object 30, the notification unit 223 notifies an administrator or other person that an abnormality has been detected.

The memory unit 201 is capable of storing various data, such as data acquired by the sensor 210 and judgment data when an abnormality is detected by the calculation unit 222.

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

The notification unit 203 is capable of notifying those in the vicinity of an abnormality if the calculation unit 222 determines that an abnormality has occurred. For example, the notification unit 203 may activate a sound generating device (such as an alarm) and/or a lighting device (such as an LED) to notify those in the vicinity of the abnormality.

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 this activation propels the piston member 10 upward within the cylinder 14 from the initial state shown in FIG. 1 . 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 (protrude) upward within the container 18. This releases the lid portion 21, opening the open end of the container 18 and ejecting the projectile 16 outward (upward in the plane of FIG. 1 ). Furthermore, negative pressure is generated in the area between the support portion 20 of the push-up member 15 and the bottom surface of the container 18, rupturing the sealing portion 40 (sealing material), allowing outside air to flow into the container 18 from outside the hole 24. The piston member 10 and tubular member 4 then move upward, but the tubular member 4 collides with the stopper member 23 and stops. If the projectile 16 is a parachute or paraglider, the projectile 16 is ejected from the container 18 and then deployed.

In this embodiment, the formation of the convex portion 18a1 and concave portion 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 friction (sliding resistance) between the parachute surface and the inner wall surface of the container more than conventionally. As a result, it is possible to provide a safety device 100 that prevents the parachute or other projectile from getting caught on the inner wall surface and allows the parachute or other projectile to be launched normally, as well as an aircraft 30 equipped with the safety device 100.

Furthermore, by reducing 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 compared to conventional methods, 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.

In addition, by reducing 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 compared to conventional methods, the projectile 16 can be launched at a faster speed than conventional methods. Therefore, if the projectile 16 is a parachute or paraglider, the time until it opens can be shortened, making it possible to reduce the altitude loss of the object on which it is placed (for example, the flying vehicle 30).

The above configuration also includes a hole 24 that connects the inside and outside of the container 18, and a sealing member 40 (sealing material) that seals the hole 24 in the initial state and breaks due to the negative pressure generated during operation in the area between the support member 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 the decline in injection performance that occurs when the container 18 does not have a hole 24. Furthermore, according to this embodiment, because the hole 24 is sealed by the sealing member 40 (sealing material) in the initial state, it is possible to prevent early deterioration or damage to the projectile 16 before operation.

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.

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 resemble a circle with a chord (a circle with a portion cut out) (see Figure 7), (2) the shape of the support portion 120 and the cover portion 121 of the push-up member 115 are shaped to match the cross section 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) multiple protrusions 118a1 and multiple recesses 118a2 are formed.

As described above, the container 118 is formed so that its cross section approximates a circle with a chord in part, but the part of the container 118 that includes the chord is a flat surface. The lid 121 is formed so that it can close the opening of the container 118.

The protrusions 118a1 have a semicircular cross-sectional shape and are arranged so that their longitudinal direction coincides with the sliding direction of the piston member 110. The recesses 118a2 are formed between adjacent protrusions 118a1, with their bottoms serving as the inner wall of the peripheral wall 118a.

This embodiment can achieve the same effects as the first embodiment.

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 above description of the embodiments, and further includes all modifications that are equivalent in meaning to and within the scope of the claims. For example, the safety device may have an ejection section that ejects projectiles into the container, and the container may have any cross-sectional shape, such as a sector or rectangle, and the lid may not close the opening of the container.

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.

While the above embodiments employ a gas generator as the power source, the configuration is not limited as long as it is capable of applying a driving force to the sliding member to propel it through the cylinder. For example, other drive sources may be used, 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. Furthermore, a retractable (also called a pulling) type retractable launcher may be used instead of the launcher in the above embodiments and variations. Examples of retractable launchers include a system in which a rocket is launched and a parachute is retracted, a system in which a weight is launched using an actuator and then a parachute is retracted, a system in which a projectile is launched using an actuator and then a parachute is retracted, and a system in which a pilot chute housed in a separate container is first launched by the launcher, and then the pilot chute is used to retract the parachute from the container of the present invention.

Furthermore, in each of the above embodiments, if a parachute or paraglider is used as the projectile, the parachute or paraglider may be packed. Note that the packing is configured to tear or peel off when activated.

Furthermore, while the above embodiments have described parachutes and paragliders as projectiles, the projectiles may also include lift-generating members. Examples of lift-generating members include parafoils, Rogallo parachutes, single-surface parachutes, airplane wings, propellers, and balloons. Furthermore, if the lift-generating member has control lines, the safety device should preferably be equipped with a steering mechanism that can use the control lines to change the inclination angle of the launched lift-generating member. This steering mechanism may, for example, include multiple reels that reel in the control lines connected to the lift-generating member, and a motor that powers these reels. By driving the motor to reel in or release the control lines, the lift-generating member can be tensioned or released as needed.

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

The aircraft may also be equipped with a safety device that uses an actuator to launch a deflated or folded float together with a drive mechanism (such as an inflation device including a gas generator), allowing the drive mechanism to inflate and deploy the float. This prevents the aircraft from sinking and can serve as a marker for where to retrieve the aircraft if it crashes.

The aircraft may also be equipped with a safety device that uses an actuator to launch a deflated or folded life jacket (float) and parachute along with a drive mechanism (such as an inflation device including a gas generator), and then deploy the life jacket and parachute using the drive mechanism. This reduces the aircraft's falling speed when it crashes, prevents the aircraft from sinking, and can also serve as a marker for where to retrieve the aircraft if it crashes.

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

Also, the flying vehicle 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. Note that a paramotor is a device that uses thrust generated by a power source (such as a motor-driven propeller rotation device) attached to the harness of the parachute or paraglider, enabling it to fly.

The flying object may also be equipped with a safety device that uses an actuator to launch a sound generating device together with a drive mechanism (including a drive unit such as a power source), and that activates the sound generating device via the drive mechanism when the flying object crashes, thereby alerting those in the vicinity to danger.

The aircraft may also be equipped with a safety device that uses an actuator to launch a lighting device (such as a flashlight) along 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 in the vicinity to danger.

The aircraft may also 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 via the drive mechanism when the aircraft crashes, spraying a fire extinguishing agent onto the aircraft body and surrounding area.

The aircraft may also be equipped with a safety device that uses an actuator to launch a pre-launched payload (such as expensive equipment) with a parachute along with a drive mechanism, and then deploys the parachute of the payload using the drive mechanism. This allows for focused protection of the payload.

The aircraft may also be equipped with a safety device that uses an actuator to eject a pre-installed, ejectable payload (such as an expensive piece of equipment) equipped with an airbag device along with a drive mechanism (such as an inflation device including a gas generator), and then inflates and deploys the airbag of the payload using the drive mechanism. This allows for focused protection of the payload.

The aircraft may also be equipped with a safety device that uses an actuator to launch a distress signal transmitter together with a drive mechanism (including a drive unit such as a power source), and that activates the distress signal transmitter via the drive mechanism in the event of a crash, allowing a distress signal to be transmitted to the outside. This makes it possible to identify the point of crash if the aircraft crashes.

The aircraft 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) along 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 aircraft crashes. This allows for the primary protection of the black box with a parachute, and as a result, flight data can be protected.

(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 convex and concave shapes 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 comparative example. The tensile tests were conducted three times to determine the tensile force (N) required to pull the piston member upward at a speed of 200 mm/min from a state in which 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) equipped with a piston member and a booster member. The tensile force was measured using a Shimadzu Corporation precision universal testing machine, model AGX-20kNVD. Table 1 also shows the results of the tensile tests. Before being placed in the container, the projectile was placed at 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 an accordion-like shape (with a wavy cross section). In this test, the parachute folded in this manner was removed from the cylindrical member and placed in a test container, and the test was conducted.

The results in Table 1 show that Examples 1 and 2 of the present invention can significantly 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 (comparison example).

Furthermore, based on the results in Table 1, it can be seen that 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 launched with a tensile strength (average) of 44 N or less, the projectile can be launched smoothly. For example, even if an example projectile is a parachute made of a relatively flexible material, 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 launched with a tensile strength (average) of 44 N or less, the parachute can be launched smoothly.

1, 101 Actuator 2, 102 Base 2A, 102A Cylindrical member 2B, 102B Flange portion 2a, 102a Hole portion 2c, 102c Insertion port 3, 103 Cylindrical member 4, 104 Tubular member 5, 105 Holding member 6, 106 Space 10, 110 Piston member 10a, 110a Main body portion 10b, 110b Rod-shaped portion 10c, 110c Hole portion 10d, 110d Female thread portion 10e, 110e Groove portion 11, 12, 111, 112 Sealing member 13, 113 Hole portion 14, 114 Cylinder 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 portion 18a1, 118a1 Convex portion 18a2, 118a2 Concave portion (groove portion)
18b, 118b Bottom 19, 119 Bottomed cylindrical portion 19a, 119a Bottom 20, 120 Support portion 21, 121 Lid portion 22, 122 Connector 22a, 122a Main body 22c, 24, 25, 26, 51, 52, 53 Hole portion 23, 123 Stopper member 23a, 23b, 123a, 123b Groove portion 27, 127 Movement prevention member 28, 128 Bolt 29, 129 Hole 30 Aircraft 31 Airframe 33 Leg portion 40 Sealing portion 50 Bolt member 50a Head portion 50b Male thread portion 53a Insertion opening 60 Blocking member 100, 300 Safety device 200 Abnormality detection device 201 Memory unit 202 Flight control unit 203 Notification unit 210 Sensor 220 Control unit 221 Abnormality detection unit 222 Calculation unit 223 Notification unit

Claims (7)

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. The safety device described in claim 1, characterized in that if the convex portion includes corners, the corners are rounded. 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 . an aircraft including an airframe, the 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 including an abnormality detection device capable of detecting an abnormality in the surrounding environment;
The safety device according to claim 1, wherein the abnormality detection device activates the actuator when the abnormality is detected. The safety device described in claim 4, further comprising a flight control unit that stops a propulsion device provided on the aircraft when the abnormality detection device detects an abnormality. 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 . 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.