Safety devices for aircraft, and aircraft equipped with safety devices for aircraft

Abstract

To provide a safety device which eliminates a need of connecting a connection member to an air vehicle and enables easy attachment work to the air vehicle, and to provide an air vehicle including the safety device.SOLUTION: A safety device 100 includes: an actuator 1: a push-up member 15 which is pushed up in one direction by the actuator 1; an injection object 16 which is pushed up supported by the push-up member 15; a storage vessel 18 which houses the actuator 1, the push-up member 15, and the injection object 16 and has a bottomed cylindrical shape; and a lid part 21 which closes an opening end of the storage vessel 18. A bottom part of a base 2 is provided with a jig 61 which moors the other end of a bridle line 70 connected at one end to the injection object 16 in the storage vessel 18, and a closing tool 62.SELECTED DRAWING: Figure 1

Description

Technical Field

[0001] The present invention relates to a safety device for ejecting ejectiles such as parachutes or paragliders, and an aircraft equipped with the safety device.

Background Art

[0002] In recent years, with the development of autonomous control technology and flight control technology, the industrial use of aircraft equipped with a plurality of rotors, such as drones, for example, has been accelerating. A drone flies, for example, by simultaneously rotating a plurality of rotors in a balanced manner, and ascending and descending are performed by increasing or decreasing the rotational speed of the rotors, and forward and backward movement can be achieved by tilting the fuselage through increasing or decreasing the rotational speed of the rotors. Such aircraft are expected to expand globally in the future.

[0003] On the other hand, the risk of a falling accident of the above-described aircraft is regarded as dangerous, which has hindered the popularization of the aircraft. In order to reduce such a risk of a falling accident, a parachute device for an aircraft is being commercialized as a safety device.

[0004] For example, as an example of the above-described parachute safety device, the applicant has filed an application related to Patent Document 1 below. As shown in FIG. 1 of Patent Document 1 below, the safety device of Patent Document 1 includes a piston member (sliding member), a cylinder that houses the piston member and is provided with a hole for the piston member to protrude outward during operation, a pushing member that is pushed upward in one direction by the piston member, an ejectile that is pushed upward while being supported by the pushing member, and a gas generator that moves the piston member within the cylinder. The pushing member has a support portion disposed on the end side of the piston member with respect to the tip of the piston member in the moving direction of the piston member. Further, the bottom of the pushing member is fixed to the tip portion of the piston member.

Prior Art Documents

Patent Documents

[0005] [Patent Document 1] Japanese Patent Publication No. 2020-1680 [Overview of the project] [Problems that the invention aims to solve]

[0006] In safety devices such as those described in Patent Document 1, if the projectile is a parachute, the other end of a string-like connecting member called a line, which is connected to one end of the parachute, may be connected to the aircraft. In this case, the safety device must be attached to the aircraft first, and then the other end of the connecting member must be connected to the aircraft, making the installation of the safety device to the aircraft complicated. Furthermore, the fastening point of the line on the aircraft needs to have sufficient strength to withstand the energy generated when the parachute is launched from the safety device. For example, if the safety device is attached to the aircraft later, the locations where the fastening point can be installed are limited.

[0007] Therefore, the present invention aims to provide a safety device that does not require the connecting member to be connected to the aircraft, and that allows for the installation of mounting parts (fastening parts) with sufficient strength to fasten and hold the line at various positions with a relatively high degree of freedom, making it easy to attach to the aircraft, and an aircraft equipped with said safety device. [Means for solving the problem]

[0008] (1) The present invention Safety devices for aircraft related to The jig comprises an injection unit for injecting an injectable material, a container that encloses the injectable material and the injection unit, and a line to which one end is connected to the injectable material, wherein the line extends to the outside of the container through a hole provided in the container, and the other end is attached to a mounting part provided on the outside of the container, and the mounting part is provided at the bottom of the container and has a mooring part to which the other end of the line can be moored.

[0010] (2) The above (1) for aircraftIn the safety device, the mooring portion is preferably a recess having an opening formed toward the bottom side of the container, and it is preferable that the device further includes a closing device that closes the surface of the recess toward the opening while the other end of the line is moored to the recess.

[0011] (3) The above (2) for aircraft In the safety device, the shape of the closure device is the for aircraft It is preferable that the safety device is formed in a shape that matches the surface shape of the mounting position on the object to which it is attached.

[0012] (4) The present invention Safety devices for aircraft related to The device comprises an injection unit for injecting an injectable material, a container enclosing the injectable material and the injection unit, and a line with one end connected to the injectable material, wherein the line extends to the outside of the container through a hole provided in the container, and the other end is attached to a mounting portion provided on the outside of the container, the injection unit is driven by a gas generator held in a holder, one end of the holder is disposed on the outside of the bottom of the container, the rest of the holder is disposed inside the container, and the mounting portion may be provided at one end of the holder.

[0013] (5) The above (1) for aircraft In the safety device, it is preferable that a fastening portion is provided on the line, which is formed by temporarily fastening at least a portion of the line inside the container by sewing or adhesive, and that the temporary fastening is released when the device is activated.

[0014] (6) The above (5) for aircraft In the safety device, it is preferable that the fastening portion is formed by bending at least a portion of the line inside the container into a Z shape.

[0015] (7) The flying object according to the present invention includes any one of the above (1) to (6), for aircraft is provided with a safety device, and the ejecta is a parachute or a paraglider.

[0016] (8) The present invention includes an ejection part for ejecting an ejecta, a container that encloses the ejecta and the ejection part, and a line having one end connected to the ejecta. The line extends outside the container through a hole provided in the container and the other end is attached to an attachment part provided outside the container. for aircraft A flying object including a safety device, wherein the ejecta is a parachute or a paraglider, has an airframe as a main body, and for aircraft the safety device is attached to the airframe via the attachment part.

Advantages of the Invention

[0017] According to the present invention, it is not necessary to connect a connecting member to the flying object, and it is possible to provide an attachment part (fastening part) having a strength capable of fastening and holding a line at various positions with a relatively high degree of freedom, and to provide a safety device that is easy to attach to the flying object and a flying object equipped with the safety device.

Brief Description of the Drawings

[0018] [[ID=|25]] [Figure 1] It is a cross-sectional view showing a safety device according to an embodiment of the present invention. [Figure 2] It is a plan view showing a part of a jig related to the safety device of FIG. 1. [Figure 3] It is a plan view showing a part of a plug related to the safety device of FIG. 1. [Figure 4] It is a bottom view of the state before attaching the jig of the safety device of FIG. 1. [Figure 5] [[ID=|38]]It is a bottom view showing a state where a connecting member is hooked on a concave part from the state of FIG. 4 and the jig of FIG. 2 is attached. [Figure 6]This is a bottom view showing the state after the occlusion device shown in Figure 3 has been installed, compared to the state shown in Figure 5. [Figure 7] This figure shows a modified example of the bridle line used in the safety device of Figure 1, where (a) is the initial state and (b) is the state in which the fastening of the fastening part has been released. [Figure 8] This figure shows an aircraft to which the safety device shown in Figure 1 is applied. [Modes for carrying out the invention]

[0019] Hereinafter, a safety device and an aircraft according to an embodiment of the present invention will be described with reference to the drawings.

[0020] As shown in Figure 1, the safety device 100 comprises an actuator 1, a push-up member 15 that is pushed up in one direction (upward in Figure 1) by the actuator 1, an injection material 16 that is pushed up while being supported by the push-up member 15, a bottomed cylindrical container 18 that houses the actuator 1, the push-up member 15, and the injection material 16, and a lid 21 that closes the open end of the container 18. In this embodiment, the injection material 16 is a parachute or paraglider. One end of a bridle line 70, which will be described later, is connected to a line formed by combining the other ends of a plurality of suspension lines (not shown), each of which has one end connected to the other end of another.

[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 for the piston member 10 to protrude outward (upward in Figure 1) when operated; a base 2 (squib holder) to which one end of the cylinder 14 is crimped and fixed, and which is attached via a hole 25 in the center of the bottom of the housing 18; and a gas generator (micro gas generator, etc.) 17 which serves as a power source for moving the piston member 10 inside the cylinder 14.

[0022] As shown in Figures 1 and 4, the base 2 includes a substantially cylindrical member 2A that holds a gas generator 17, which generates power to slide the piston member 10, on the cylinder 14 side, and a flange portion 2B provided on the side of the substantially cylindrical member 2A opposite to the cylinder 14 side.

[0023] As shown in Figure 4, the flange portion 2B includes a plurality of holes 2a used for attachment to the housing 18 or the jig 61 described later, a plurality of holes 2b used for attachment to the top plate portion 31a of the fuselage 31 of the aircraft 30 described later, an insertion opening 2c used for inserting the connector 22 for energizing the electrode 17b at the bottom of the gas generator 17, and tip portions 2d and 2e, and is machined into a roughly U-shaped, roughly horseshoe shape (a shape in which a part of the ring shape is cut out from the outer edge to the center, forming a notch between the tip portions 2d and 2e). The inner wall of the hole portion 2a is threaded so that a bolt 28 or fixing member 64 described later can be screwed into it. Furthermore, the inner wall of the hole 2b is also threaded, allowing the fixing member 63 to be screwed into the aircraft body 30 (described later) from the aircraft body 31 side via the holes 61d and 62b provided in the jig 61 and the closure device 62 (described later), thereby fixing the base 2 to the aircraft body 31. Also, as shown in Figure 4, the tips 2d and 2e of the base 2 are formed in a rounded, curved shape (such as an R shape), which prevents damage to parts and injuries to people from contact. In addition, the space (notch) between the tips 2d and 2e is in communication with the insertion opening 2c.

[0024] As shown in Figures 1 and 4, the connector 22 comprises a main body 22a that can be inserted into the substantially cylindrical member 2A via an insertion opening 2c, a projection 22b 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 substantially cylindrical member 2A is fitted. The projection 22b is electrically connected to a connector (not shown) that connects to an external power supply via wiring 41 that extends in a direction perpendicular to the insertion direction of the connector 22 (radially from the center of the base 2 when mounted on the base 2). The main body 22a also has a hole 22c inside that is electrically connected to both the electrode 17b and the wiring 41 connected to the projection 22b. The projection 22b is shaped to match the shape of the area between the tip portions 2d and 2e of the base 2 (the area forming the aforementioned notch), and is formed to fit into the area between the tip portions 2d and 2e of the base 2 (the area forming the aforementioned notch). This allows the connector 22 to be positioned (directed) relative to the insertion port 2c. Furthermore, if the wiring 41 is moved in the circumferential direction of the base 2 after being attached to the insertion port 2c, the connector 22 will not move in the circumferential direction of the base 2, thereby preventing damage to the electrode 17b at the bottom of the gas generator 17.

[0025] Furthermore, the insertion port 2c of the base 2 and the connector 22 are configured such that, when attached to the base 2, they extend radially from the center of the base 2, so that the wiring 41 does not block the ventilation hole 24.

[0026] Furthermore, as shown in Figure 5, a jig 61 is fixed to the bottom surface of the base 2 by a fixing member 64. The jig 61 is an annular member made of metal (aluminum or iron, or an alloy), resin, or a composite material of resin and metal, CFRP, or fiber-reinforced resin. As shown in Figure 2, the jig 61 includes a recess 61a (mooring portion) to which the bridle line 70 can be moored, a hole 61b for fixing the jig 61 to the base 2 by the fixing member 64, a hole 61c for fixing the closure device 62 (described later) to the jig 61 by the fixing member 65, and a hole 61d through which the fixing member 63 passes when fixing the top plate portion 31a of the aircraft body 31 of the aircraft body 30 (described later) to the base 2 by the fixing member 63. Here, the fixing member 63 is, for example, a bolt or screw, but any member with sufficient strength and fastening force may be used. Furthermore, if the fixing member 65 is a bolt or screw, the inner wall of the hole 61c is threaded. Also, the fixing members 64 and 65 do not necessarily need to be as strong as the fixing member 63, as long as the required fastening force is met.

[0027] As shown in Figure 6, a closing device 62 is fixed to the bottom surface of the jig 61 by a fixing member 65. The closing device 62 closes the opening side of the recess 61a while the other end of the bridle line 70 is anchored to the recess 61a of the jig 61. The closing device 62 is an annular member made of metal (aluminum or iron, or an alloy), resin, or a composite material of resin and metal, CFRP, or fiber-reinforced resin. As shown in Figure 3, the closing device 62 has a pair of holes 62a for positioning when attached to the jig 61, and holes 62b and 62c through which the fixing member 63 passes when fixing the top plate portion 31a of the aircraft body 31 of the aircraft body 30 (described later) to the base 2. A communication portion 62c1 is provided in the center of hole 62c, which communicates with hole 61c when the closing device 62 is attached to the jig 61.

[0028] The bridle line 70 has an annular shape at its other end and can be attached to the recess 61a of the jig 61 so as to be anchored, as shown in Figure 5. One end of the bridle line 70 is disposed inside the container 18 via a hole 60 provided at the bottom of the container 18 and is connected to the injection mold 16.

[0029] Here, as a modification, a portion of the bridle line 70 located inside the housing 18 near the hole 60 is folded into a Z-shape, as shown in Figure 7(a), and temporarily fastened by sewing, or by bonding with adhesive or welding. This temporary fastening by sewing or bonding can be released by the tensile force applied through the suspension line (not shown) during operation, as shown in Figure 7(b), from the initial fastening portion 70a in Figure 7(a) to the release portion 70a1. In other words, in the case of temporary fastening by sewing, the strength of the sewing is set to such an extent that the bridle line 70 is pulled and the sewing breaks during operation. In the case of temporary fastening by bonding, the strength of the bonding is set to such an extent that the bridle line 70 is pulled and the bonding peels off during operation. Therefore, since the above temporary fastening can be released during operation, it does not affect the ejection of the projectile 16, and after deployment, the line (provided on parachutes, etc.) and the aircraft 30, described later, receive uniform force and become balanced. In addition, this temporary fastening prevents the bridle line 70 from being pulled out from the hole 60 of the containment container 18.

[0030] 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 threaded portion 10d provided at the upper end of the rod-shaped portion 10b, and a groove portion 10e provided in the circumferential direction of the main body portion 10a.

[0031] At least the upper end of the rod-shaped portion 10b has a non-circular cross-section, although this is not shown in the figure. Here, a non-circular shape includes, for example, a polygonal shape, an elliptical shape, a star shape, or a gear shape, but any shape that is non-circular is included. Furthermore, at the lower part of the rod-shaped portion 10b, the tubular member 4 is fitted or loosely fitted with the main body portion 10a with one end in contact. 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 within a range that does not hinder the plastic deformation due to substantially uniform compression during impact, which will be described later.

[0032] As shown in Figure 1, the tubular member 4 is held by the holding member 5 at the lower part 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 is plastically deformable and has a tensile strength lower than that of the piston member 10 and the stopper member 23 described later (for example, metals such as iron, aluminum, brass, copper, alloys such as stainless steel, resins, etc.). Here, the holding member 5 may be an elastic material such as rubber, or it may be made of the same material as the tubular member 4, and its shape may be ring-shaped or clip-shaped.

[0033] Furthermore, to prevent the tubular member 4 from contacting the inner wall of the cylinder 14, the tubular member 4 and the inner wall of the cylinder 14 are separated by a predetermined distance or more (for example, a distance at which the tubular member 4, which has undergone plastic deformation due to substantially uniform compression upon impact with the stopper member 23, will not come into contact with the inner wall of the cylinder 14). As a result, even if the tubular member 4 undergoes plastic deformation upon impact with the stopper member 23, it will deform without being hindered by the inner wall of the cylinder 14, and the impact on the piston member 10 will be sufficiently mitigated.

[0034] 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. As a result, the piston member 10 is lighter than if the hole 10c were not formed.

[0035] The female threaded portion 10d is formed from the tip of the rod-shaped portion 10b along the central axis up to a certain point. Furthermore, the male threaded portion 50b of the bolt member 50, which will be described later, can be screwed into the female threaded portion 10d.

[0036] A sealing member 11, such as an O-ring, is provided in the circumferential direction in the groove portion 10e.

[0037] A substantially cylindrical stopper member 23 is provided at the top of the cylinder 14, positioned to surround a portion of the rod-shaped portion 10b of the piston member 10. That is, the rod-shaped portion 10b is inserted through the hole 13 of the stopper member 23. The cylinder 14 is also provided with a through hole 14a for releasing air from the space 6 to the outside when it is in operation. In Figure 1, only one through hole 14a is provided, but multiple through holes may be provided in the circumferential direction.

[0038] The stopper member 23 restricts the movement of the tubular member 4 to the cylinder 14 and has a groove 23a along the outer circumference and a groove 23b along the inner circumference. The groove 23a is used to crimp and fix the other end of the cylinder 14 to the stopper member 23. A sealing member 12, such as an O-ring, is provided in the circumferential direction of the groove 23b.

[0039] The cylinder 14 may be made of a material and its outer wall thickness may be appropriately adjusted so that it can undergo plastic deformation in the radial direction if the piston member 10 of the actuator 1 becomes immobile for any reason, and the initial combustion volume of the actuator 1 is reduced, causing the gunpowder to burn and generating a combustion pressure exceeding the pressure resistance value of the cylinder 14 (an abnormal situation). Examples of materials that make up the cylinder 14 include metals such as iron, aluminum, brass, and copper, and alloys such as stainless steel. As a result, in the above abnormal situation, the cylinder 14 undergoes plastic deformation in the radial direction, which reduces (mitigates) 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 the generated gas can pass. Therefore, by allowing the gas generated during the above-mentioned abnormal situation to leak out through this gap, the gas is released to the outside of the cylinder 14 from the through-hole 14a, and then released to the outside of the container 18 through the ventilation hole 24 via the gap between the outer wall of the cylinder 14 and the inner wall of the bottomed cylindrical part 19, thus preventing the cylinder 14 from rupturing (fail-safe function). In the case of this fail-safe function, a space (gap) is provided between the outer wall of the cylinder 14 and the inner wall of the bottomed cylindrical part 19 that allows the cylinder 14 to undergo sufficient plastic deformation in the radial direction.

[0040] 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 of the piston member 10, which will be described later. Furthermore, 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.

[0041] The push-up member 15 is made of metal (aluminum or iron, or an alloy), resin, or a composite material of resin and metal, CFRP or fiber-reinforced resin, and as shown in Figure 1, it has a bottomed cylindrical portion 19 that covers a part of the cylinder 14, that is, the outer part of the cylinder 14 excluding the area near the open end on the side where the gas generator 17 is located, and a disc-shaped support portion 20 that is provided as a flange (flange-shaped portion) at the opening of the bottomed cylindrical portion 19 to support the injection material 16.

[0042] The bottomed cylindrical portion 19 has a bottom portion 19a that is roughly flat or roughly columnar (roughly columnar in this embodiment), a hole portion 51 formed on the lid portion 21 side of the bottom portion 19a, a hole portion 52 (second hole portion) with a smaller diameter than the hole portion 51, and a hole portion 53 (first hole portion) that communicates with the hole portion 51 via the hole portion 52 and has a larger diameter than the hole portion 52. The hole portion 51 has a diameter larger than the diameter of the head portion 50a of the bolt member 50. The hole portion 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 portion 51 side to the hole portion 53 side. The hole 53 is substantially the same shape as one end (upper end) of the rod-shaped portion 10b, and when one end of the rod-shaped portion 10b is inserted through the insertion opening 53a provided on the cylinder 14 side of the bottom 19a of the bottomed cylindrical portion 19, it becomes a fitting portion into which one end of the rod-shaped portion 10b fits.

[0043] 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 screwing it into the female threaded portion 10d of the fitted rod-shaped portion 10b in the hole 53. At this time, one end of the rod-shaped portion 10b is non-circular and is fitted into the hole 53 which is substantially the same shape, so when the bolt member 50 is screwed into the female threaded portion 10d, the rod-shaped portion 10b does not rotate together. Specifically, because the tip of the push-up member 15 and the tip of the piston member 10 are non-circular and fit together, when fastening with the bolt member 50, the push-up member 15 can be rotated while being fixed, and the piston member 10 can be tightened toward the gas generator 17 without rotating together.

[0044] The support portion 20 is initially positioned spaced apart from the inner bottom surface of the container 18. The support portion 20 also has ventilation holes 26 to reduce the effect of negative pressure generated between the bottom of the injectable 16 and the support portion 20 during operation, thereby facilitating the injection of the injectable 16. The outer circumference of the support portion 20 is formed so as not to come into contact with the inside of the container 18. At least one (eight in this embodiment) movement prevention member 27 is provided on the upper surface of the support portion 20 to prevent the bottomed cylindrical portion 19 of the injectable 16 from moving in the circumferential direction.

[0045] The movement prevention members 27 are roughly triangular in shape, made of resin, or a composite material of resin and metal, CFRP, or fiber-reinforced resin, and are provided in multiple quantities so as to be rotationally symmetrical with respect to the bottomed cylindrical portion 19. In addition, ventilation holes 26 are provided between each of these movement prevention members 27. Here, as an example, only one movement prevention member 27 may be provided. Even in this case, multiple ventilation holes 26 are provided in the support portion 20.

[0046] As shown in Figure 1, the bottom of the container 18 is provided with a plurality of ventilation holes 24 that connect the inside and outside of the container 18, a hole 25 into which the base 2 is inserted, and holes 29 for bolt fastening. Also, as shown in Figure 1, the bottom of the container 18 has a recess in the center, and this center and the area around it form at least two steps. When the push-up member 15 moves rapidly inside 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. By providing the ventilation holes 24, the negative pressure phenomenon can be reduced, and the push-up member 15 can be moved smoothly. In addition, the hole 25 is closed by fastening the hole 2a provided in the flange portion of the base 2 located on the outside of the bottom of the container 18 with bolts 28 through the hole 29 from the inside of the container 18. Furthermore, by reducing the distance between the support portion 20 and the bottom surface inside the container 18, the injection material 16 is prevented from falling onto the bottom surface inside the container 18.

[0047] Furthermore, the ejected material 16 is housed within the containment container 18, between the inner surface of the containment container 18 and the outer surface of the bottomed cylindrical portion 19 of the push-up member 15, for example, surrounding the outer surface of the bottomed cylindrical portion 19. The ejected material 16 is also folded so that its outer surface does not come into contact with the inside of the containment container 18. The ejected material 16 is connected to one end of a string (not shown), for example, and the other end of the string is connected to the inside of the containment container 18 (for example, tied to the support portion 20 via a plurality of ventilation holes 26) or to the airframe 31 of the aircraft 30, which will be described later. Here, as one modification, the ejected material 16 may be folded so that its outer surface comes into contact with the inside of the containment container 18.

[0048] The gas generator 17 may use only an igniter, or it may be a gas generator equipped with both an igniter and a gas generating agent. Alternatively, a hybrid or stored-type gas generator may be used, which uses a gunpowder-type igniter to break the seal plate in a small gas cylinder and discharge the gas inside to the outside. In this case, the pressurized gas in the gas cylinder can be a non-flammable gas such as argon, helium, nitrogen, or carbon dioxide, or a mixture thereof. Furthermore, to ensure that the piston is reliably propelled when the pressurized gas is released, the gas generator may be equipped with a heating element made of a gas generating agent composition or a thermite composition, etc.

[0049] The injection unit that ejects the material 16 mainly consists of a piston member 10, a cylinder 14, a push-up member 15, a gas generator 17, etc.

[0050] In the configuration described above, when the gas generator 17 is activated when an aircraft, for example, equipped with the safety device 100, falls, the pressure of the gas generated by the activation propels the piston member 10 upward within the cylinder 14. As a result, the push-up member 15, which has a bottomed cylindrical portion 19 connected to the rod-shaped portion 10b of the piston member 10, is propelled upward (protrudes) within the containment 18. This causes the lid 21 to detach, the open end of the containment 18 to open, and the ejected object 16 is ejected outward from the containment 18 (upward in the plane of Figure 1). At this time, the piston member 10 and the tubular member 4 move upward, but the tubular member 4 collides with the stopper member 23 and stops. If the ejected object 16 is a parachute or paraglider, the ejected object 16 is deployed after being ejected from the containment 18. Subsequently, when tension (tensile force) is applied to the suspension line and bridle line 70, at least the fixing member 63 receives this tension.

[0051] As shown in Figure 1, the safety device 100 is connected and fixed to the top plate portion 31a of the aircraft body 31 of the aircraft body 30 by a fixing member 63 from the aircraft body 31 side via the hole 62b of the closure device 62, the hole 61d of the jig 61, and the hole 2b of the base 2. At this time, as shown in Figure 1, the base 2 connects the housing 18 and the aircraft body 31 in a position that does not block the ventilation holes 24. Therefore, as shown in Figure 8, the aircraft body 30 comprises the aircraft body 31, the safety device 100 connected to the aircraft body 31, one or more propulsion mechanisms (e.g., propellers, etc.) 32 connected to the aircraft body 31 and propelling the aircraft body 31, and a plurality of legs 33 provided on the lower part of the aircraft body 31.

[0052] Furthermore, although not shown in Figure 8, the safety device 100 on such an aircraft 30 can be installed with the wiring 41 and connector (not shown) extending horizontally in Figure 8. Therefore, it can be configured to easily connect to wiring (not shown) taken out from any part of the aircraft body 31. Also, since the only part that avoids the wiring on the top of the aircraft 30 is the base 2, the space between the bottom surface of the housing 18 and the top surface of the aircraft 30 can be effectively utilized.

[0053] As described above, according to this embodiment, it is not necessary to connect connecting members such as the bridle line 70 to the aircraft body 31 of the aircraft 30, and by using the jig 61, the safety device 100 can be made easier to attach to the aircraft 30. Furthermore, if it is preferable to connect the bridle line 70 to the aircraft body 31 of the aircraft 30, this can be done by removing the jig 61 and the closure device 62 and connecting the other end of the bridle line 70 to a preferred location on the aircraft body 31. In other words, according to this embodiment, the attachment point for connecting members such as the bridle line 70 can be provided at various locations on the aircraft 30 or the safety device 100 with a relatively high degree of freedom.

[0054] Furthermore, after the injection material 16 is ejected from the container 18, it is unfolded, and subsequently, tension (tensile force) is applied to the suspension line and bridle line 70. At this time, by designing the fixture 63 to be able to withstand this tension alone (considering the strength of the fixture 63), it becomes unnecessary to consider the strength of the jig 61. In other words, the jig 61 only needs to be strong enough to anchor the bridle line 70 in its initial state, making the design simpler. In this case, if the jig 61 is made of a relatively lightweight material such as resin, the safety device 100 will be relatively lightweight. Of course, the jig 61 may be made of a relatively high-strength material if necessary.

[0055] Furthermore, a portion of the connector 22 (the part connected to the wiring 41) is shaped to match the shape between the tip portions 2d and 2e of the base 2. This allows for the positioning (direction setting) of the connector 22 relative to the insertion port 2c. In addition, if the wiring 41 is moved in the circumferential direction of the base 2 after being attached to the insertion port 2c, the connector 22 will not move in the circumferential direction of the base 2, thereby preventing damage to the electrode 17b at the bottom of the gas generator 17.

[0056] Furthermore, since the flange portion 2B of the base 2 is provided on the outside of the bottom of the housing 18, the base 2 can be directly attached to the airframe 31 of the aircraft 30. As a result, the recoil during operation is received directly by the airframe 31, rather than through the housing 18, but the impact on the housing 18 during operation can be reduced, so the strength of the bottom of the housing 18 can be reduced compared to when the base 2 is provided inside the housing 18. In other words, the strength of the bottom of the housing 18 can be safely reduced compared to before (for example, by designing it so that the thickness of the bottom of the housing 18 is reduced to a safe predetermined thickness), and the housing 18 as a whole can be made lighter than before while ensuring the same level of safety as before. In addition, since a step is provided on the bottom surface of the housing 18, the strength of the bottom surface of the housing 18 can be strengthened compared to a flat surface without a step.

[0057] Furthermore, since the connector 22 has a distinctive shape with a protrusion 22b, it is possible to prevent incorrect insertion of the connector.

[0058] Furthermore, the power wiring for the safety device 100 on the aircraft 30 does not necessarily need to be located directly below the safety device 100. Therefore, this contributes to the ease of designing the aircraft 30.

[0059] Furthermore, since the tips of each base 2 are rounded (R-shaped), compared to a shape where the fan-shaped portion is simply cut straight from the outside of a circular shape toward the center (where the tips have sharp angles), it is possible to prevent the base 2 from scratching each other during manufacturing (such as when they are in a parts feeder).

[0060] Furthermore, when the connector 22 is attached to the base 2, the wiring 41 extends radially from the center of the base 2, making wiring easier. Also, since the wiring 41 is arranged so as not to block the ventilation holes 24, it does not interfere with the function of the ventilation holes 24.

[0061] Furthermore, an aircraft 30 equipped with a safety device 100 having the configuration described above can be obtained.

[0062] Although 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 indicated by the claims rather than the above description of embodiments, and all modifications within the meaning and scope equivalent to the claims are included. For example, the present invention includes the following modifications:

[0063] In the above embodiment, the bottom surface of the fastener 62 was flat to match the shape of the top plate portion 31a of the aircraft body 31 of the aircraft 30, but it is not limited to this. That is, the shape of the bottom surface of the fastener 62 may be changed to match the surface shape of the position on the aircraft body 31 (object to be attached) to which it is to be attached. Also, if the fastener 62 is made of resin, it is easier to form the shape of the bottom surface of the fastener 62 into various shapes, thus increasing its versatility to a wider variety of aircraft. If the fixing member 63 is designed to withstand the tension from the suspension line and bridle line 70, the strength of the fastener 62, together with the jig 61, only needs to be strong enough to tether the bridle line 70 in its initial state.

[0064] Furthermore, the bridle line may extend to the outside of the container through a hole provided in one of the container's locations (bottom, side, etc.), and the other end may be attached to a mounting part (a protrusion, recess, etc., or any part that can be hooked or tied to secure the other end of the bridle line) provided in one of the container's locations (bottom, side, etc.) or on the base (squib holder).

[0065] Furthermore, although the bridle line 70 was anchored to the recess 61a in the above embodiment, the recess does not have to be a recess shape, as long as the fixing member 63 can receive the tension and the other end of the bridle line 70 can be anchored to it.

[0066] Furthermore, in the above embodiment, a portion of the base 2 was configured to be located outside the container 18, but the entire base 2 may be configured to be located inside the container 18. In this case, the jig and the closure device are configured to be fixed to the base inside the container via the bottom of the container.

[0067] Furthermore, although a gas generator was used as the power source in each of the above embodiments, the configuration is not limited as long as it is possible to provide the sliding member with the driving force necessary for the sliding member to propel itself within the cylinder. For example, an elastic type using an elastic body such as a spring, a gas cylinder type using gas pressure confined in a container, or a chemical reaction type (non-explosive) that generates gas pressure by mixing two or more substances and causing a chemical reaction may be used as the power source. In addition, a pull-out type (also called a tension type) ejection device may be used instead of the ejection device of the above embodiments and modified examples. Examples of such pull-out type ejection devices include a method in which a rocket is launched and a parachute is pulled out, a method in which a weight is launched with an actuator and then a parachute is pulled out, a method in which a projectile is launched with an actuator and then a parachute is pulled out, and a method in which a pilot chute, which is initially housed in another container, is launched by the ejection device, and the parachute is pulled out from the container according to the present invention by the pilot chute.

[0068] Furthermore, although the container 18 is formed in a cylindrical shape in the above embodiment, it is not limited to this and may be formed in other shapes, such as a square tube.

[0069] Furthermore, in each of the above embodiments, if a parachute or paraglider is used as the projectile, the parachute or paraglider may be packed. The packing is configured to tear or peel off during operation.

[0070] Furthermore, while the above embodiments mention parachutes or paragliders as the ejected objects, the invention is not limited to these, and objects including lift-generating members may also be ejected. Examples of lift-generating members include parafoils, Rogallo-type parachutes, single-surface parachutes, airplane wings, propellers, balloons, etc. If the lift-generating member has a control line, it is desirable that the safety device includes a steering mechanism that can use the control line to change the inclination angle of the ejected lift-generating member. This steering mechanism may include, for example, a plurality of reels that wind up a plurality of control lines connected to the lift-generating member, and a motor that powers these reels. By winding up or unwinding the control lines by driving the motor, the lift-generating member can be pulled or released as appropriate.

[0071] Alternatively, the aircraft may be equipped with a safety device capable of launching a net instead of a parachute or paraglider. By launching the net at the right time towards a hook or protrusion, the aircraft can be hooked onto the hook or protrusion. As a result, the aircraft can be prevented from falling and crashing to the ground.

[0072] Furthermore, the aircraft may be equipped with a safety device that allows an actuator to eject a deflated or folded lifebuoy (float) along with a drive mechanism (such as an inflation device including a gas generator), and the drive mechanism to inflate and unfold the lifebuoy. This prevents the aircraft from sinking and also serves as a marker for the recovery location in the event of a crash.

[0073] Furthermore, the aircraft may be equipped with a safety device that allows an actuator to eject a retracted or folded lifebuoy (float) and parachute together with a drive mechanism (such as an inflation device including a gas generator), and the drive mechanism to deploy the lifebuoy and parachute. This reduces the falling speed of the aircraft when it crashes, prevents the aircraft from sinking into water, and also serves as a marker for the recovery location in the event of a crash.

[0074] Alternatively, the aircraft may be equipped with a safety device that allows an actuator to eject a parachute along with a drive mechanism (such as a cutting device with a drive unit), and after the parachute is deployed, the drive mechanism cuts some of the multiple connecting members that connect the parachute to the aircraft, shifting the aircraft's center of gravity so that it falls sideways, and then using an airbag device provided on the side of the aircraft that is falling to mitigate the impact of a collision with the ground or the like.

[0075] Alternatively, the aircraft may be equipped with a safety device that allows an actuator to eject a so-called paramotor along with its drive mechanism (including a power supply and other drive components), 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 can fly by obtaining thrust from a power source (such as a motor-driven propeller rotater) attached to the harness portion of a parachute or paraglider.

[0076] Furthermore, the aircraft may be equipped with a safety device that allows an actuator to eject a sound-generating device along with a drive mechanism (including a power supply and other drive components), and the drive mechanism to activate the sound-generating device when the aircraft crashes, thereby alerting those in the surrounding area of ​​danger.

[0077] Furthermore, the aircraft may be equipped with a safety device that allows an actuator to eject a lighting device (such as a flashlight) along with a drive mechanism (including a power supply and other drive components), and the drive mechanism to activate the lighting device when the aircraft crashes, thereby alerting those in the surrounding area to danger.

[0078] Alternatively, the aircraft may be equipped with a safety device that allows an actuator to eject a fire extinguisher along with a drive mechanism (including a power supply and other drive components), and the drive mechanism to activate the fire extinguisher in the event of a crash, thereby spraying fire extinguishing agent onto the aircraft and its surroundings.

[0079] Alternatively, the aircraft may be equipped with a safety device that uses an actuator to eject a pre-launched, ejectable payload with a parachute (for example, expensive equipment) along with a drive mechanism, and the drive mechanism deploys the parachute of the payload. This allows for focused protection of the parachute payload.

[0080] Alternatively, the aircraft may be equipped with a safety device that uses an actuator to eject an airbag-equipped payload (for example, expensive equipment) that has been pre-loaded in a ejectable manner, along with a drive mechanism (such as an inflation device including a gas generator), and inflates and deploys the airbag of the airbag-equipped payload. This allows for focused protection of the airbag-equipped payload.

[0081] Alternatively, the aircraft may be equipped with a safety device that allows an actuator to eject a distress signal transmitter along with a drive mechanism (including a power supply and other drive components), and the drive mechanism to activate the distress signal transmitter when the aircraft crashes, thereby transmitting a distress signal to the outside. This makes it possible to pinpoint the crash site if the aircraft crashes.

[0082] Alternatively, the aircraft may be equipped with a safety device that uses an actuator to eject 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 the drive mechanism to deploy the parachute of the black box when the aircraft crashes. This allows for focused protection of the black box with the parachute. As a result, flight data can be protected. [Explanation of Symbols]

[0083] 1 Actuator 2 bases 2A, 3 Cylindrical members 2B Flange section 2a, 2b, 10c, 22c, 25, 51, 52, 53, 60, 61b, 61c, 61d, 62a, 62b, 62c Hole 2c insertion slot 2d, 2e tip 4 Tubular member 5. Retaining member 6 Space 10 Piston member 10a, 22a Main body 10b Rod-shaped part 10d Female thread section 10e, 23a, 23b groove 11, 12 Sealing members 13 Hole 14 cylinders 14a Through hole 15 Push-up member 16 Projectile 17 Gas generator 17a Cup body 17b Electrode 18 containers 19 Bottomed cylindrical part 19a bottom 20 Support part 21 Lid 22 connectors 22b Protrusion 23 Stopper member 24, 26 Ventilation holes 27 Movement prevention member 28 volts 29 holes 30 flying objects 31 aircraft 33 Legs 41 Wiring 50 Bolt Members 50a Head section 50b Male threaded section 53a Insertion opening 62c1 Communication part 63, 64, 65 Fixing members 70 Bridle Line 70a Fastening part 70a1 Release part 100 safety equipment

Claims

1. An injection unit that ejects the material, A container that encloses the injection material and the injection unit, A line to which one end is connected to the aforementioned injection material, Equipped with, The line extends to the outside of the housing through a hole provided in the housing, and its other end is attached to a mounting portion provided on the outside of the housing. The safety device for an aircraft is characterized in that the mounting portion is a jig provided at the bottom of the housing and has a mooring portion capable of mooring the other end of the line.

2. The mooring portion is a recess having an opening formed toward the bottom side of the container, The safety device for an aircraft according to claim 1, further comprising a closing device that closes the opening side of the recess while the other end of the line is anchored to the recess.

3. The aircraft safety device according to claim 2, characterized in that the shape of the blocking device is formed to match the surface shape of the mounting position of the object to which the aircraft safety device is attached.

4. An injection unit that ejects the material, A container that encloses the injection material and the injection unit, A line to which one end is connected to the aforementioned injection material, Equipped with, The line extends to the outside of the housing through a hole provided in the housing, and its other end is attached to a mounting portion provided on the outside of the housing. The injection unit is driven by a gas generator held in a holder. One end of the holder is disposed on the outside of the bottom of the container, and the rest of the holder is disposed inside the container. The safety device for an aircraft is characterized in that the mounting portion is provided at one end of the holder.

5. A fastening portion is provided on the line, which is formed by temporarily securing at least a portion of the line inside the container by sewing or adhesive. The safety device for an aircraft according to claim 1, characterized in that the temporary fastening is released when the device is activated.

6. The safety device for an aircraft according to claim 5, characterized in that the fastening portion is formed by bending at least a portion of the line inside the housing into a Z shape.

7. The aircraft safety device is provided according to any one of claims 1 to 6, The aforementioned projectile is a flying object characterized by being a parachute or a paraglider.

8. An aircraft safety device comprising: an injection unit for ejecting an injectable object; a container enclosing the injectable object and the injection unit; and a line to which one end is connected to the injectable object, wherein the line extends to the outside of the container through a hole provided in the container and the other end is attached to a mounting part provided on the outside of the container, and the injectable object is a parachute or a paraglider, The aforementioned flying object has a main body, The aircraft is characterized in that the safety device for the aircraft is attached to the aircraft via the mounting portion.

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