Safety device and aircraft with same

Abstract

[Problem] To provide a safety device that makes it possible to easily attach an aircraft without connecting a connecting member to the aircraft, and to provide an aircraft provided with the safety device. [Solution] A safety device (100) is provided with: an actuator (1); a push-up member (15) that is pushed up in one direction by the actuator (1); an ejection object (16) supported and pushed up by the push-up member (15); a closed-end cylindrical container (18) that accommodates the actuator (1), the push-up member (15), and the ejection object (16); and a lid section 21 that closes the open end of the container 18. The bottom of the base (2) is provided with a clip (61) that captures the other end of a tie line (70), one end of which is connected to the shot (16) in the container (18), and a stopper (62).

Description

Technical Field

[0001] The present invention relates to a safety device for ejecting ejected objects such as parachutes and 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 with multiple rotors, such as drones, has also accelerated. For example, drones fly by rotating multiple rotors in a balanced manner at the same time, and can rise and fall by increasing or decreasing the number of rotor rotations, and can move forward and backward by tilting the body by increasing or decreasing the number of rotor rotations. It is foreseeable that this type of aircraft will develop globally in the future.

[0003] On the other hand, the risk of the above-mentioned aircraft crash is considered to be very dangerous, which hinders the popularization of aircraft. In order to reduce the risk of such crash, aircraft parachute devices are being commercialized as safety devices.

[0004] For example, as an example of the above-mentioned parachute safety device, the applicant has applied for the following patent document 1. The safety device of the patent document 1 is as follows: Figure 1 As shown, it comprises: a piston member (sliding member); a cylinder that accommodates the piston member and is provided with a hole for the piston member to protrude outward during operation; a push-up member that is pushed in one direction by the piston member; an ejection object that is supported and pushed up by the push-up member; and a gas generator that moves the piston member in the cylinder, the push-up member having a support portion that is arranged on the end side of the piston member based on the front end of the piston member in the moving direction of the piston member. In addition, the bottom of the push-up member is fixed to the tip of the piston member.

[0005] Prior art literature

[0006] Patent Literature

[0007] Patent Document 1: Japanese Patent Application Publication No. 2020-1680 Summary of the invention

[0008] Problem that the invention aims to solve

[0009] In the safety device such as Patent Document 1, if the ejected object is a parachute, etc., the other end of a rope-shaped connecting member called a line connected to one end of the parachute is sometimes connected to the aircraft. In this case, the other end of the connecting member needs to be connected to the aircraft after the safety device is installed on the aircraft, which makes the installation of the safety device on the aircraft complicated. In addition, the strength of the fastening part of the line in the aircraft must be sufficient to withstand the energy generated when the parachute of the safety device is ejected. For example, if the safety device is to be installed on the aircraft, the place where the fastening part is set will be limited.

[0010] Therefore, an object of the present invention is to provide a safety device that does not require a connecting component to be connected to an aircraft and can provide an installation portion (fastening portion) with a strength that can fasten and hold a wire at various positions with a relatively high degree of freedom, thereby facilitating installation operations on the aircraft, and an aircraft equipped with the safety device.

[0011] Solutions to the problem

[0012] (1) The present invention is characterized in that it comprises an ejection unit that ejects an ejection object; a container that contains the ejection object and the ejection unit; and a wire, one end of which is connected to the ejection object, the wire is extended to the outside of the container through a hole provided in the container, and the other end is mounted on a mounting portion provided on the outside of the container.

[0013] (2) In the safety device of (1) above, the attachment portion is preferably a clamp provided at the bottom of the storage container and having a mooring portion capable of mooring the other end of the wire.

[0014] (3) In the safety device of (2) above, the mooring portion is preferably a recessed portion having an opening formed toward the bottom side of the storage container, and the safety device further includes a closing member that closes the surface of the opening side of the recessed portion while the other end of the wire is moored in the recessed portion.

[0015] (4) In the safety device of (3) above, it is preferable that the blocking member has a shape that matches a surface shape of a mounting position of an object to which the safety device is mounted.

[0016] (5) In the safety device of (1) above, the ejection portion preferably uses a gas generator held on a bracket as a driving force, one end of the bracket is arranged on the outside of the bottom of the container, the portion other than the one end of the bracket is arranged in the container, and the mounting portion is arranged on one end of the bracket.

[0017] (6) In the safety device of (1) above, it is preferred that a fixing portion is provided on the wire for temporarily fixing at least a portion of the wire inside the container by sewing or bonding, and the temporary fixing is released during operation.

[0018] (7) In the safety device of (6) above, the fixing portion preferably forms at least a portion of the wire inside the container in a Z-shape while being bent.

[0019] (8) The aircraft of the present invention is characterized in that it has the safety device described in any one of (1) to (7), and the projectile is a parachute or a paraglider.

[0020] (9) The aircraft of (8) above preferably has an airframe as a main body, and the safety device is mounted on the airframe via the mounting portion.

[0021] Effects of the Invention

[0022] The present invention can provide a safety device that does not require connecting components to an aircraft and can provide a mounting portion (fastening portion) with a strength capable of fastening and retaining a wire at various positions with a relatively high degree of freedom, thereby facilitating installation operations on the aircraft, as well as an aircraft equipped with the safety device. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] [ Figure 1 ] is a cross-sectional view showing a safety device according to an embodiment of the present invention.

[0024] [ Figure 2 ] is shown Figure 1 A plan view of a portion of a clamp of a safety device.

[0025] [ Figure 3 ] is shown Figure 1 A plan view of a portion of an occlusive piece of a safety device.

[0026] [ Figure 4 ] is shown Figure 1 A bottom surface diagram of a state before the clamp of the safety device is installed.

[0027] [ Figure 5 ] is to show from Figure 4 The connecting part is hooked into the recess and installed. Figure 2 Bottom surface diagram of the state of the fixture.

[0028] [ Figure 6 ] is to show that from Figure 5 Status Installed Figure 3 Bottom surface diagram of the state of the occluder.

[0029] [ Figure 7 ] is shown in Figure 1 Figure 1 shows a modified example of a tie line used in a safety device.

[0030] (a) is an initial state, and (b) is a diagram showing a state where the fastening of the fixing portion is released.

[0031] [ Figure 8 ] is shown Figure 1 A diagram of the aircraft to which the safety device is applicable. DETAILED DESCRIPTION

[0032] A safety device and an aircraft according to embodiments of the present invention will be described below with reference to the drawings.

[0033] like Figure 1 As shown, the safety device 100 comprises an actuator 1; an upward push member 15, which is pushed by the actuator 1 in one direction ( Figure 1 The push-up member 15 is a member for pushing up the ejection object 16; the ejection object 16 is supported and pushed up by the push-up member 15; a bottomed cylindrical container 18 is provided to accommodate the actuator 1, the push-up member 15 and the ejection object 16; and a cover 21 is provided to close the open end of the container 18. In addition, in the present embodiment, the ejection object 16 is a parachute or a paraglider. In the parachute or the paraglider, a line formed by the other ends of a plurality of suspension lines (not shown) connected at one end of each of the plurality of suspension lines is connected to one end of a traction line 70 described later.

[0034] The actuator 1 comprises a piston member 10, which serves as a sliding member; a cylinder 14, which accommodates the piston member 10 and is provided with a function for causing the piston member 10 to move outward during operation ( Figure 1 a base 2 (igniter bracket) to which one end of the cylinder 14 is riveted and fixed and installed via a hole 25 in the center of the bottom of the receiver 18; and a gas generator (micro gas generator, etc.) 17, which serves as a power source for moving the piston component 10 in the cylinder 14.

[0035] like Figure 1 and Figure 4 As shown, the base 2 includes: a proximal cylindrical member 2A that holds a gas generator 17 that generates power to slide the piston member 10 on the cylinder 14 side; and a flange portion 2B that is provided on the side of the proximal cylindrical member 2A opposite to the cylinder 14 side.

[0036] like Figure 4As shown, the flange 2B has a plurality of holes 2a for mounting on the storage container 18 or the jig 61 described later, a plurality of holes 2b for mounting on the top plate 31a of the body 31 of the aircraft 30 described later, an insertion 2c for inserting the power supply connector 22 into the electrode 17b at the bottom of the gas generator 17, and tip portions 2d and 2e, which are processed into a nearly U-shaped horseshoe shape (a shape such as a notch formed between the tip portions 2d and 2e by cutting off a portion of the ring from the outer edge to the center). An internal thread is cut on the inner wall of the hole 2a, so that it can be screwed with the bolt 28 or the fixing member 64 described later. In addition, an internal thread is also cut on the inner wall of the hole 2a, and the fixing member 63 is screwed with the aircraft 30 described later from the body 31 side through the holes 61d and 62b provided on the jig 61 and the closing member 62 described later, so that the base 2 can be fixed to the body 31. In addition, if Figure 4 As shown, the tip portions 2d and 2e of the base 2 are formed into a smooth curved shape (R shape, etc.), thereby preventing damage to parts and human body caused by contact, etc. In addition, the space (cutout portion) between the tip portions 2d and 2e is connected to the insertion port 2c.

[0037] like Figure 1 and Figure 4 As shown, the connector 22 includes a main body 22a that can be inserted into the proximal cylindrical part 2A through the insertion port 2c; a protrusion 22b that protrudes from the side surface of the lower part of the main body 22a; and a hole 22c in which the electrode 17b located in the proximal cylindrical part 2A is inserted. The protrusion 22b is electrically connected to a connector (not shown) connected to an external power source via a wiring 41 extending in a direction perpendicular to the insertion direction of the connector 22 (in a radial direction from the center of the base 2 when mounted on the base 2). In addition, a hole 22c is provided inside the main body 22a, which is electrically connected to both the electrode 17b and the wiring 41 connected to the protrusion 22b. The shape of the protrusion 22b imitates the shape between the tip portions 2d and 2e of the base 2 (the portion forming the above-mentioned cutout portion), and is formed by fitting between the tip portions 2d and 2e of the base 2 (the portion forming the above-mentioned cutout portion). In this way, the position of the connector 22 relative to the insertion port 2c can be positioned (oriented). Furthermore, when the wiring 41 moves in the circumferential direction of the base 2 after being attached to the insertion port 2 c , the connector 22 does not move in the circumferential direction of the base 2 , thereby preventing the lower electrode 17 b of the gas generator 17 from being damaged.

[0038] Furthermore, the insertion port 2 c of the base 2 and the connector 22 are configured to extend radially from the center of the base 2 when mounted on the base 2 , so that the wiring 41 is arranged so as not to block the ventilation hole 24 .

[0039] In addition, if Figure 5As shown in FIG. 6 , the clamp 61 is fixed to the bottom surface of the base 2 by a fixing member 64. The clamp 61 is an annular member made of metal (aluminum or iron, etc., or alloy), resin, or a composite material such as resin and metal, CFRP or fiber reinforced resin. Figure 2 As shown, the clamp 61 has: a recess 61a (tethering portion) that can tie the traction line 70; a hole 61b for fixing the clamp 61 to the base 2 through a fixing member 64; a hole 61c for fixing the closure member 62 described later to the clamp 61 through a fixing member 65; and a hole 61d for passing the fixing member 63 when the top plate portion 31a of the fuselage 31 of the aircraft 30 described later is fixed to the base 2 through the fixing member 63. Here, the fixing member 63 is, for example, a bolt, a screw, etc., but any member can be used as long as it has sufficient strength and tightening force. In addition, when the fixing member 63 is a bolt or a screw, an internal thread is cut on the inner wall of the hole 61c. In addition, the fixing members 64 and 65 do not necessarily need to have the same strength as the fixing member 63, as long as they can achieve a given tightening force.

[0040] like Figure 6 As shown, the other end of the pulling wire 70 is tied to the concave portion 61a of the clamp 61, and the blocking member 62 that blocks the surface of the opening side of the concave portion 61a is fixed to the bottom surface of the clamp 61 by the fixing member 65. The blocking member 62 is an annular member made of metal (aluminum or iron, etc., or alloy), resin, or a composite material such as resin and metal, CFRP or fiber reinforced resin. Figure 3 As shown, the blocking member 62 includes a pair of holes 62a for determining the position when the blocking member 62 is mounted on the fixture 61, and holes 62b and 62c for allowing the fixing member 63 to pass through when the top plate 31a of the body 31 of the aircraft 30 described later is fixed to the base 2 by the fixing member 63. A connecting portion 62c1 is provided at the center of the hole 62c, which is connected to the hole 61c when the blocking member 62 is mounted on the fixture 61.

[0041] The other end of the traction wire 70 is formed into a ring shape. Figure 5 As shown, it can be attached to the recess 61a of the clamp 61. In addition, one end side of the pull wire 70 is arranged inside the container 18 through the hole 60 provided at the bottom of the container 18, and is connected to the projectile 16.

[0042] Here, as a modified example, Figure 7 As shown in (a), a portion of the pulling wire 70 disposed inside the storage container 18, i.e., near the hole 60, is formed into a Z-shaped curved portion and temporarily fixed by suturing (sewing) or bonding with an adhesive or welding. In addition, the temporary fixation by sewing or bonding can be achieved by applying a tensile force through the above-mentioned suspension wire (not shown) during operation, such as Figure 7 (b) shows that Figure 7 The above-mentioned temporary fixation is released by changing the fixing portion 70a in the initial state of (a) to the state of the releasing portion 70a1. That is, when the temporary fixation is produced by sewing, the strength of the sewing is set to such an extent that the traction line 70 is stretched during operation and the sewing is damaged. In addition, when the temporary fixation is produced by bonding, the strength of the bonding is set to such an extent that the traction line 70 is stretched during operation and the bonding is peeled off. Therefore, since the temporary fixation can be released during operation, the temporary fixation does not affect the ejection of the ejection object 16. After deployment, the line (the line set on the parachute, etc.) and the flying object 30 described later are evenly stressed and balanced. In addition, by such temporary fixation, it is possible to prevent the traction line 70 from being pulled out of the hole 60 of the storage container 18.

[0043] The piston member 10 includes a main body portion 10a having an outer diameter substantially 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; an internal thread portion 10d provided at the upper end portion of the rod-shaped portion 10b; and a groove portion 10e provided in the circumferential direction of the main body portion 10a.

[0044] Although not shown, the cross section of at least the upper end side of the rod-shaped portion 10b is formed into a non-circular shape. Here, the so-called non-circular shape includes, for example, a polygon, an ellipse, a star shape, or a gear shape, and any non-circular shape is included as long as it is a non-circular shape. In addition, in the lower part of the rod-shaped portion 10b, the tubular member 4 is tightly embedded or loosely embedded in a state where one end is in contact with the main body 10a. In addition, there may be a gap between the inner wall of the tubular member 4 and the outer wall of the rod-shaped portion 10b, and the gap can be within a degree that does not hinder the plastic deformation caused by the approximately uniform compression during the collision described later.

[0045] like Figure 1 As shown, the tubular member 4 is held at the lower part of the rod-shaped portion 10b by the holding member 5 in a state where one end is in contact with the main body 10a. In addition, the tubular member 4 is a plastically deformable material and is made of a material (for example, metals such as aluminum, brass, and copper, alloys such as stainless steel, and resins) having a lower tensile strength than the piston member 10 and the stopper member 23 described later (for example, metals such as iron, aluminum, brass, and copper, alloys such as stainless steel, and resins such as single-piece cast nylon, nylon 6, nylon 6,6, and polyamide synthetic resins such as nylon 4,6). Here, the holding member 5 may be an elastic member such as rubber, or may be made of the same material as the tubular member 4, and may be in a ring shape or a clip shape.

[0046] In addition, in order to prevent the tubular member 4 from contacting the inner wall of the cylinder 14, 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, which is plastically deformed by substantially uniform compression when colliding with the stopper 23, does not contact the inner wall of the cylinder 14). Thus, even if the tubular member 4 collides with the stopper 23 and is plastically deformed, it is not hindered by the inner wall of the cylinder 14 and deformed, thereby sufficiently alleviating the impact of the piston member 10.

[0047] The hole 10c is formed along the central axis from the lower end of the main body 10a to the middle of the rod-shaped portion 10b. As a result, the weight of the piston member 10 is reduced compared to a case where the hole 10c is not formed.

[0048] The internal thread portion 10d is formed from the tip of the rod-shaped portion 10b to the middle along the central axis. The internal thread portion 10d can be screwed with the external thread portion 50b of the bolt member 50 described later.

[0049] A sealing member 11 such as an O-ring is provided in the circumferential direction of the groove portion 10e.

[0050] A substantially cylindrical stopper member 23 is provided at the upper portion of the cylinder 14 so as to surround a portion of the rod-shaped portion 10b of the piston member 10. That is, the rod-shaped portion 10b is arranged in a state of being inserted through the hole 13 of the stopper member 23. In addition, a through hole 14a is provided in the cylinder 14 for releasing the air in the space 6 to the outside during operation. Figure 1 Although only one through hole 14a is provided in the structure, a plurality of through holes 14a may be provided in the circumferential direction.

[0051] The stopper member 23 restricts the movement of the tubular member 4 within the cylinder 14, and has a groove 23a provided along the outer circumference and a groove 23b provided along the inner circumference. The groove 23a is used to rivet and fix the other end of the cylinder 14 to the stopper member 23. In addition, a sealing member 12 such as an O-ring is provided in the circumferential direction on the groove 23b.

[0052] When the piston member 10 of the actuator 1 cannot move for some reason, and when the initial combustion volume of the actuator 1 is reduced and the gunpowder burns to generate a combustion pressure that is higher than the withstand pressure value of the cylinder 14 (when an abnormal situation occurs), the cylinder 14 can be appropriately adjusted in terms of material selection and the thickness of the outer peripheral portion so that it can be plastically deformed in the radial direction of the cylinder 14. Examples of materials constituting the cylinder 14 include metals such as iron, aluminum, brass, and copper, and alloys such as stainless steel. Thus, when the above-mentioned abnormal situation occurs, since the cylinder 14 can be plastically deformed in the radial direction, the sealing performance of the sealing member 12 such as the O-ring is reduced (relaxed), and a gap can be formed between the sealing member 12 and the inner wall of the cylinder 14 through which the generated gas can pass. Therefore, by allowing the generated gas to leak out from the gap when the above-mentioned abnormal situation occurs, the gas is released from the through hole 14a to the outside of the cylinder 14, passes through the inside of the accommodating container 18 from the gap between the outer wall of the cylinder 14 and the inner wall of the bottomed cylindrical portion 19, and is released to the outside of the accommodating container 18 from the vent hole 24, thereby preventing the cylinder 14 from breaking (failure protection function). In addition, when the 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 cylindrical portion 19 so that the cylinder 14 can be fully plastically deformed in the radial direction.

[0053] The gas generator 17 is arranged below the main body 10a of the piston member 10 in a state of being pressed into the lower opening end of the cylinder 14. Also, a cylindrical member 3 is provided around the cup 17a of the gas generator 17 to form a predetermined distance from the piston member 10.

[0054] The push-up member 15 is made of metal (aluminum or iron, etc., or alloy), resin, or a composite material of resin and metal, CFRP or fiber-reinforced resin, etc. Figure 1 As shown, it has: a bottomed cylindrical portion 19, which is configured in a manner to cover a portion of the cylinder 14, that is, the outer portion of the cylinder 14 except for the opening end on the side where the gas generator 17 is configured; and a disc-shaped supporting portion 20, which is provided as a flange (flange-like portion) at the opening portion of the bottomed cylindrical portion 19 and supports the ejection object 16.

[0055] The bottomed cylindrical portion 19 has: a bottom portion 19a, which is a nearly flat plate shape or a nearly cylindrical shape (in the present embodiment, a nearly cylindrical shape); a hole portion 51, which is formed on the cover portion 21 side of the bottom portion 19a; a hole portion 52 (a second hole portion), which has a smaller diameter than the hole portion 51; and a hole portion 53 (a first hole portion), which is connected to the hole portion 51 through the hole portion 52 and has a larger diameter than the hole portion 52. The hole portion 51 has a larger diameter than the cap portion 50a of the bolt member 50. The hole portion 52 has a smaller diameter than the cap portion 50a, and can guide the external thread portion 50b of the bolt member 50 inserted from the hole portion 51 side to the hole portion 53 side. The hole 53 has substantially the same shape as one end (upper end) of the rod-shaped portion 12 and becomes a fitting portion that fits one end of the rod-shaped portion 12 by inserting one end of the rod-shaped portion 12 from an insertion opening 53a provided on the cylinder 14 side of the bottom 19a of the bottomed cylindrical portion 19.

[0056] The bolt component 50 connects the rod-shaped portion 10b and the push-up component 15 by inserting the external thread portion 50b from the hole portion 51 side into the hole portion 52 and screwing it with the internal thread portion 10d of the rod-shaped portion 10b that is engaged with the hole portion 53. At this time, one end of the rod-shaped portion 10b is non-circular and is engaged with the hole portion 53 of substantially the same shape, so when the bolt component 50 and the internal thread portion 10d are screwed together, the rod-shaped portion 10b does not rotate together. Specifically, because the tip portions of the push-up component 15 and the piston component 10 are non-circular and are engaged, when fastened with the bolt component 50, the push-up component 15 can be fixed while being rotated, and the piston component 10 can be fastened in a manner that does not tighten in the direction of the gas generator 17 and rotate together.

[0057] In the initial state, the support portion 20 is separated from the bottom inner surface of the storage container 18. In addition, the support portion 20 has a vent hole 26 for reducing the influence of the negative pressure generated between the bottom of the ejection object 16 and the support portion 20 during operation, so that the ejection object 16 is easier to eject. In addition, the outer peripheral portion of the support portion 20 is formed in a manner that does not contact the inner side of the storage container 18. In addition, 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 ejection object 16 from moving in the surrounding direction of the bottomed cylindrical portion 19.

[0058] The movement preventing member 27 is a nearly triangular member made of a resin or a composite material of a resin and metal, CFRP or fiber reinforced resin, etc., and is provided in plurality and is provided in a rotationally symmetrical manner with the bottomed cylindrical portion 19 as the center. In addition, a through hole 26 is provided at each interval of the above-mentioned movement preventing member 27. Here, as a modified example, only one movement preventing member 27 may be provided. In this case, a plurality of through holes 26 are provided in the support portion 20.

[0059] like Figure 1As shown, the bottom of the container 18 is provided with a plurality of vent holes 24 communicating the inside and outside of the container 18, a hole 25 for inserting the base 2, and a hole 29 for bolt fastening. Figure 1 As shown, the central portion of the bottom of the receiver 18 is a recessed portion, and the central portion and the surrounding of the central portion form a stepped shape of at least two levels. In addition, when the push-up component 15 moves quickly in the receiver 18, a negative pressure is generated in the area between the push-up component 15 and the bottom surface of the receiver 18. As a result, the push-up component 15 is difficult to move. Therefore, by providing the above-mentioned vent 24, the negative pressure phenomenon can be alleviated, allowing the push-up component 15 to move smoothly. In addition, the hole 25 is blocked by fastening the hole 2a in the flange portion of the base 2 located on the outer side of the bottom of the receiver 18 with a bolt 28 through the hole 29 from the inner side of the receiver 18. In addition, by shortening the distance between the support portion 20 and the bottom surface on the inner side of the receiver 18, the ejected object 16 is prevented from falling to the bottom surface on the inner side of the receiver 18.

[0060] In addition, the ejection 16 is contained in the receptacle 18, for example, between the inner surface of the receptacle 18 and the outer surface of the bottomed cylindrical portion 19 of the push-up member 15 in a manner surrounding the outer surface of the bottomed cylindrical portion 19. In addition, the ejection 16 is folded in a manner in which its outer side does not contact the inner side of the receptacle 18. In addition, the ejection 16 is connected to, for example, one end of a thin wire (not shown in the figure), and the other end of the thin wire is connected to the inside of the receptacle 18 (for example, fixed to the support portion 20 via a plurality of ventilation holes 26) or to the body 31 of the aircraft 30 described later. Here, as a modified example, the ejection 16 may also be folded in a state in which its outer side contacts the inner side of the receptacle 18.

[0061] The gas generator 17 may use only an igniter, or may use a gas generator having an igniter and a gas generating agent. In addition, a hybrid type or storage type gas generator may be used, which uses a gunpowder type igniter to crack the sealing plate in a small gas cylinder and discharge the internal gas to the outside. At this time, as the pressurized gas in the gas cylinder, non-flammable gases such as argon, helium, nitrogen, carbon dioxide, or their mixtures may be used. In addition, in order to reliably advance the piston when releasing the pressurized gas, the gas generator may also be provided with a heating element composed of a gas generating agent composition or a thermite composition.

[0062] The ejection portion for ejecting the ejected material 16 is mainly composed of the piston member 10, the cylinder 14, the push-up member 15, the gas generator 17, and the like.

[0063] In the above structure, when the aircraft equipped with the safety device 100 falls, the gas generator 17 operates, and the gas pressure generated by the operation pushes the piston member 10 upward in the cylinder 14. As a result, the push-up member 15 having the bottomed cylindrical portion 19 connected to the rod-shaped portion 10b of the piston member 1o is pushed upward (protruded) in the container 18. As a result, the cover 21 is detached, so that the open end of the container 18 is opened, and the projectile 16 is ejected from the inside of the container 18 to the outside ( Figure 1 At this time, the piston member 10 and the tubular member 4 move upward, but the tubular member 4 hits the brake member 23 and stops. Furthermore, when the projectile 16 is a parachute or a paraglider, the projectile 16 is deployed after being ejected from the container 18. Thereafter, when tension (pulling force) is applied to the suspension line and the traction line 70, at least the fixing member 63 is subjected to the tension.

[0064] In addition, if Figure 1 As shown, the safety device 100 is connected and fixed to the top plate 31a of the body 31 of the aircraft 30 by the fixing member 63 from the body 31 side through the hole 62b of the blocking member 62, the hole 61d of the clamp 61, and the hole 2b of the base 2. Figure 1 As shown, the base 2 connects the container 18 and the body 31 at a position that does not block the vent hole 24. Figure 8 As shown, the aircraft 30 includes a body 31 , a safety device 100 coupled to the body 31 , one or more propulsion mechanisms (such as propellers, etc.) 32 coupled to the body 31 and propelling the body 31 , and a plurality of legs 33 disposed at the lower portion of the body 31 .

[0065] In addition, although Figure 8 30, but the safety device 100 in such an aircraft 30 may be Figure 8 The wiring 41 and the connector (not shown) are pulled out in the lateral direction of the aircraft 30. Therefore, it is easy to connect to the wiring (not shown) taken out from any of the bodies 31 of the aircraft 30. In addition, since only the base 2 portion is a portion away from the wiring in the upper part of the aircraft 30, the remaining space between the bottom surface of the storage container 18 and the upper surface of the aircraft 30 can be effectively used.

[0066] As described above, according to the present embodiment, it is not necessary to connect the connecting member such as the pull wire 70 to the body 31 of the aircraft 30, and by using the clamp 61, it is possible to realize the safety device 100 that can be easily mounted on the aircraft 30. In addition, if it is preferred to connect the pull wire 70 to the body 31 of the aircraft 30, the clamp 61 and the blocking member 62 may be removed, and the other end of the pull wire 70 may be connected to a preferred portion of the corresponding body 31 for adjustment. That is, according to the present embodiment, the mounting portion for mounting the connecting member such as the pull wire 70 can be set at various positions of the aircraft 30 or the safety device 100 with a relatively high degree of freedom.

[0067] In addition, after the ejection object 16 is ejected from the storage container 18 and unfolded, tension (pulling force) is applied to the suspension line and the traction line 70. At this time, it is designed that the fixing component 63 can withstand the tension alone (considering the strength of the fixing component 63), so there is no need to consider the strength of the clamp 61. That is, the clamp 61 only needs to have sufficient strength to retain the traction line 70 in the initial state and be easy to design. At this time, if the clamp 61 is made of a relatively lightweight material such as resin, the safety device 100 will also become relatively lightweight. In addition, of course, the clamp 61 can also be made of a material with relatively high strength as needed.

[0068] In addition, a portion of the connector 22 (the portion connected to the wiring 41) is shaped to follow the shape between the tip portions 2d and 2e of the base 2. Thus, the connector 22 can be positioned (oriented) relative to the insertion port 2c. In addition, when the wiring 41 moves in the circumferential direction of the base 2 after being mounted in the insertion port 2c, the connector 22 does not move in the circumferential direction of the base 2, thereby preventing the electrode 17b at the bottom of the gas generator 17 from being damaged.

[0069] In addition, since the flange portion 2B of the base 2 is arranged outside the bottom of the container 18, the base 2 can be directly mounted on the body 31 of the aircraft 30. As a result, the recoil force during operation is not borne by the container 18 but directly by the body 31. Since the impact on the container 18 during operation can be reduced, the strength of the bottom of the container 18 can be reduced compared to the case where the base 2 is arranged inside the container 18. That is, compared with the past, the strength of the bottom of the container 18 can be safely reduced (for example, as a design to reduce the thickness of the bottom of the container 18 to a safe given thickness), while ensuring the same safety as before, the container 18 can be made lighter than before. In addition, since a step is provided on the bottom surface of the container 18, the strength of the bottom surface of the container 18 can be enhanced compared to a flat bottom surface without a step.

[0070] In addition, since the connector 22 has a unique shape with the protrusion 22b, it is possible to prevent the connector from being mistakenly inserted.

[0071] In addition, the power supply wiring for the safety device 100 on the aircraft 30 side does not necessarily need to be provided directly below the safety device 100. Therefore, this contributes to a simpler design of the aircraft 30.

[0072] In addition, since the tip portions of the bases 2 are each formed into a rounded shape (R-shape), it is possible to prevent the bases 2 from being damaged by each other during manufacturing (for example, when being placed in a parts feeder, etc.), compared to a shape obtained by simply cutting the fan-shaped portion straightly from the outside of the circle to the center (a shape with an acute angle at the tip).

[0073] Furthermore, when the wiring 41 connected to the connector 22 is mounted on the base 2, the wiring is easier because it is radially extended from the center of the base 2. In addition, since the wiring 41 is arranged so as not to block the vent hole 24, the function of the vent hole 24 is not hindered.

[0074] Furthermore, it is possible to obtain the aircraft 30 including the safety device 100 having the above-described structure.

[0075] Although the embodiments of the present invention are described above based on the drawings, the specific configuration is not limited to the above embodiments. The scope of the present invention is not shown by the description of the above embodiments but by the claims, and includes all changes within the meaning and scope equivalent to the claims. For example, the present invention includes the following modifications.

[0076] In the above-mentioned embodiment, the bottom surface of the blocking member 62 is a plane to match the shape of the top plate portion 31a of the body 31 of the aircraft 30, but it is not limited to this. That is, the shape of the bottom surface of the blocking member 62 can be changed to match the surface shape of the desired installation position of the body 31 (the object to be installed). In addition, if the blocking member 62 is made of resin, the shape of the bottom surface of the blocking member 62 can be easily formed into various shapes, thereby improving the versatility of use in various aircraft. In addition, if the fixing member 63 is designed to withstand the tension generated by the suspension line and the traction line 70, the strength of the blocking member 62 together with the clamp 61 only needs to be a strength to the extent that the traction line 70 can be tied in the initial state.

[0077] In addition, the traction wire can be extended to the outside of the receiver through a hole set at any part of the receiver (bottom, side, etc.), and the other end can be installed at any part of the outside of the receiver (bottom, side, etc.) or a mounting part on the base (igniter bracket) (a convex part, concave part, etc. that can fix the other end of the traction wire by means of hooking or bundling).

[0078] In the above embodiment, the pulling wire 70 is tied to the recessed portion 61 a . However, as long as the fixing member 63 can withstand the tension and be formed to tie the other end of the pulling wire 70 , it does not need to be in a recessed shape.

[0079] In the above embodiment, a part of the base 2 is located outside the container 18, but the entire base 2 may be located inside the container 18. In this case, the clamp and the obturator are fixed to the base inside the container via the bottom of the container.

[0080] In addition, in each of the above-mentioned embodiments, a gas generator is used as a power source, but as long as the driving force for pushing the sliding part to slide in the cylinder can be applied to the sliding part, its structure is not limited. For example, an elastic body type using an elastic body such as a spring, a gas cylinder type using the gas pressure blocked in a container, a chemical reaction type (non-explosive) in which two or more substances are mixed and chemically reacted to generate gas pressure, and other driving sources may be used. In addition, a pull-out type (also called a stretching type) injection device may be used to replace the injection device of the above-mentioned embodiment and the modified example. As such a pull-out type injection device, for example, there can be cited: a method of pulling out a parachute by making a rocket fly out, a method of pulling out a parachute after a heavy object is made to fly out by an actuator, a method of pulling out a parachute after a projectile is made to fly out by an actuator, a method of first ejecting a pilot chute stored in another container by an injection device and using the pilot chute to pull out the parachute from the container of the present invention, etc.

[0081] In addition, in the above-mentioned embodiment, the container 18 is formed in a cylindrical shape, but it is not limited to this, and it may be another shape, such as a square tube.

[0082] In addition, in each of the above-mentioned embodiments, when a parachute or a paraglider is used as the ejection object, the parachute or the paraglider can be packaged. In addition, the packaging is configured to destroy or peel off during operation.

[0083] Furthermore, in the above-mentioned embodiment, the ejected object is listed as a parachute or a paraglider, but it is not limited thereto, and an object including a lift generating component may also be ejected as an ejected object. The lift generating component may be, for example, a parafoil, a logaro parachute, a single-surface parachute, an airplane wing, a propeller, a balloon, etc. In addition, when the lift generating component has a control line, it is desirable that the safety device has a steering mechanism that can change the tilt angle of the ejected lift generating component by using the control line. The steering mechanism, for example, has a plurality of reels that are respectively wound around a plurality of control lines connected to the lift generating component, and a motor that serves as the power of these reels, and by driving the motor to wind or pull out the control line, the lift generating component can be appropriately stretched or loosened.

[0084] In addition, instead of a parachute or a paraglider, an aircraft may be provided with a safety device capable of ejecting a net. Thus, if the net is ejected toward a hook or a protrusion at the right time, the aircraft can be caught on the hook or the protrusion. As a result, the aircraft can be prevented from falling toward the ground and colliding.

[0085] In addition, the aircraft may be equipped with such a safety device that can eject the contracted or folded floating ring (float) together with the driving mechanism (including an expansion device such as a gas generator, etc.) through an actuator, and expand and unfold the floating ring through the driving mechanism. This can prevent the aircraft from being submerged in water and can serve as a mark for the recovery position when the aircraft falls.

[0086] In addition, there may be an aircraft equipped with such a safety device, which can eject the retracted or folded floating ring (float) and parachute together with the driving mechanism (including an expansion device such as a gas generator, etc.) through an actuator, and expand the floating ring and parachute through the driving mechanism. In this way, the falling speed of the aircraft can be reduced when it falls, and the aircraft can be prevented from being submerged in water, and can serve as a mark of the recovery position when the aircraft falls.

[0087] Alternatively, the aircraft may be provided with a safety device that can eject a parachute together with a drive mechanism (including a cutting device of a drive portion, etc.) through an actuator; after the parachute is deployed, the drive mechanism cuts off a portion of a plurality of connecting components connecting the parachute to the aircraft, causing the center of gravity of the aircraft to shift and fall sideways; and then, an airbag device provided on the side of the falling side of the aircraft is used to mitigate the impact of a collision with the ground, etc.

[0088] In addition, it can also be an aircraft equipped with such a safety device, which can eject the so-called power parachute together with the drive mechanism (including drive components such as a power source) through an actuator, and after the parachute or paraglider is fully deployed, the drive mechanism drives the motor to rotate the propeller. As a result, the parachute or paraglider will not be entangled in the propeller. In addition, the so-called power parachute refers to a device that is capable of flying by providing a power (such as a propeller rotating machine based on a motor) in the harness part of the parachute or paraglider to obtain thrust.

[0089] Alternatively, the aircraft may be equipped with a safety device that can emit a sound generating device together with a driving mechanism (including driving components such as a power source) through an actuator, and activate the sound generating device through the driving mechanism when the aircraft falls, thereby notifying the surroundings of the danger.

[0090] Alternatively, the aircraft may be equipped with a safety device that can emit a lighting device (such as a flashlight) together with a driving mechanism (including driving components such as a power supply) through an actuator, and activate the lighting device through the driving mechanism when the aircraft falls, thereby notifying the surroundings of the danger.

[0091] In addition, it may also be an aircraft equipped with such a safety device, which can eject the fire extinguisher together with the driving mechanism (including driving components such as a power supply) through an actuator, and activate the fire extinguisher through the driving mechanism when the aircraft falls, thereby spraying the fire extinguishing agent onto the aircraft body and its surroundings.

[0092] In addition, there may be an aircraft equipped with such a safety device, which can eject a parachute-carrying object (e.g., expensive equipment) pre-installed in an ejectable manner together with a driving mechanism through an actuator, and deploy the parachute of the parachute-carrying object through the driving mechanism. Thus, the parachute-carrying object can be protected intensively.

[0093] In addition, there may be an aircraft equipped with such a safety device, which can eject a previously ejectable object with an airbag device (e.g., expensive equipment) together with a driving mechanism (including an expansion device such as a gas generator) through an actuator, and inflate and deploy the airbag of the object with the airbag device through the driving mechanism. Thus, the object with the airbag device can be protected intensively.

[0094] In addition, there may also be an aircraft equipped with such a safety device, which can eject the distress signal sending device together with the driving mechanism (including driving components such as a power supply) through an actuator, and activate the distress signal sending device through the driving mechanism when the aircraft falls, so that a distress signal can be sent to the outside. In this way, when the aircraft falls, the crash site can be determined.

[0095] In addition, there may be an aircraft equipped with such a safety device, which can eject a black box with a parachute (flight recorder, etc.) together with a drive mechanism (including an expansion device such as a gas generator, etc.) through an actuator, and the parachute of the black box with a parachute can be deployed through the drive mechanism when the aircraft falls. In this way, the black box with a parachute can be protected emphatically. As a result, flight data can be protected.

[0096] Explanation of symbols

[0097] 1 Actuator

[0098] 2 abutment

[0099] 2A, 3 Cylindrical parts

[0100] 2B Flange

[0101] 2a, 2b, 10c, 22c, 25, 51, 52, 53, 60, 61b, 61c, 61d, 62a, 62b, 62c Cave

[0103] 2c Insertion port

[0104] 2d, 2e Tip

[0105] 4 Tubular parts

[0106] 5. Keeping components

[0107] 6. Space

[0108] 10 Piston parts

[0109] 10a, 22a Main body

[0110] 10b Rod-shaped part

[0111] 10d Internal thread

[0112] 10e, 23a, 23b groove

[0113] 11, 12 Sealing parts

[0114] 13 Hole

[0115] 14 Cylinders

[0116] 14a Through hole

[0117] 15 Push-up component

[0118] 16 Ejaculation

[0119] 17 Gas Generator

[0120] 17a Cup body

[0121] 17b Electrode

[0122] 18 Storage

[0123] 19 bottomed cylindrical part

[0124] 19a Bottom

[0125] 20 Support Department

[0126] 21 cover

[0127] 22 Connectors

[0128] 22b Protrusion

[0129] 23 Brake parts

[0130] 24, 26 Ventilation holes

[0131] 27 Movement prevention parts

[0132] 28 Bolt

[0133] 29 holes

[0134] 30 Aircraft

[0135] 31 Body

[0136] 33 Legs

[0137] 41 Wiring

[0138] 50 Bolt Parts

[0139] 50a Head

[0140] 50b External thread

[0141] 53a Insertion opening

[0142] 62c1 Connecting part

[0143] 63, 64, 65 fixed parts

[0144] 70 Pull Line

[0145] 70a Fixed part

[0146] 70a1 Release Department

[0147] 100 Safety Devices

Claims

1. A safety device, characterized in that: have an ejection portion that ejects an ejection; a container containing the ejected object and the ejecting portion, and A line, one end of which is connected to the ejection object, The wire is extended to the outside of the receiver through a hole provided on the receiver, and the other end is installed on a mounting portion provided on the outside of the receiver.

2. The safety device according to claim 1, characterized in that: The mounting portion is a clamp provided at the bottom of the storage container and having a tying portion capable of tying the other end of the wire.

3. The safety device according to claim 2, characterized in that: The anchoring portion is a recessed portion having an opening formed toward the bottom side of the storage container. The safety device further includes a closing member that closes a surface of the recessed portion on the opening side in a state in which the other end of the wire is tied to the recessed portion.

4. The safety device according to claim 3, characterized in that: The blocking member is formed in a shape that matches the surface shape of the mounting position of the object to which the safety device is mounted.

5. The safety device according to claim 1, characterized in that: The ejection unit uses a gas generator held on a bracket as a driving force. One end of the bracket is arranged outside the bottom of the storage container, and the portion other than the one end of the bracket is arranged inside the storage container. The mounting portion is arranged on one end of the bracket.

6. The safety device according to claim 1, characterized in that: The thread is provided with a fixing portion for temporarily fixing at least a portion of the thread inside the storage container by sewing or bonding. During operation, the temporary fixation is released.

7. The safety device according to claim 6, characterized in that: The fixing portion forms at least a portion of the wire in the container into a Z-shape in a bent state.

8. An aircraft, characterized in that A safety device according to any one of claims 1 to 7, The projectile is a parachute or a paraglider.

9. The aircraft according to claim 8, characterized in that: The aircraft has a body as a main body, The safety device is installed on the machine body via the installation portion.

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