Safety devices, and aircraft equipped with safety devices

Abstract

The present invention provides a safety device that can improve waterproof performance while suppressing a decrease in ejection performance, and an aircraft equipped with the safety device. [Solution] The safety device 100 comprises a piston member 10, an actuator 1 having a gas generator 17 that generates a driving force to slide the piston member 10 to one side, a support part 20 that extends from the piston member 10 so as to be movable together with the piston member 10 when in operation and supports the injection material 16, a bottomed cylindrical container 18 having a bottom and sides, which houses at least the piston member 10, the actuator 1, the support part 20, and the injection material 16 inside, and which has one or more holes 24a, 24b penetrating the bottom and sides of the container, in the part closer to the bottom than the support part 20, and a closing part 40 that is breathable and waterproof and is provided to close the holes 24a, 24b.

Description

Technical Field

[0001] The present invention relates to a safety device 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, has been accelerating. A drone flies by, for example, rotating a plurality of rotors in balance at the same time, ascending and descending by increasing and decreasing the rotational speed of the rotors, and moving forward and backward by tilting the aircraft through increasing and decreasing the rotational speed of the rotors. Such an aircraft is not only used for disaster operations, cargo transportation, landscape photography, etc., but also assumed to carry passengers, and is expected to be widely used worldwide in the future.

[0003] On the other hand, the risk of a falling accident of the above-described aircraft is regarded as dangerous, etc., which has hindered the spread of the aircraft. To reduce such a risk of a falling accident, etc., safety devices such as a parachute device for an aircraft are being commercialized.

[0004] For example, Patent Document 1 discloses a safety device including an actuator, a pushing member pushed upward in one direction by the actuator, a projectile supported and pushed upward by the pushing member, and a bottomed cylindrical container. The container has a plurality of hole portions at the bottom, and in an initial state, each of the hole portions is sealed by a sealing portion. The sealing portion breaks due to a negative pressure generated during operation in a region between the support portion and the bottom surface of the container. When the sealing portion breaks, outside air flows in through the hole portions.

Prior Art Documents

Patent Documents

[0005]

Patent Document 1

Summary of the Invention

[0006] Incidentally, in safety devices, there is a need to improve waterproofing performance while suppressing a decrease in injection performance.

[0007] Therefore, the present invention aims to provide a safety device that can improve waterproof performance while suppressing a decrease in ejection performance, and an aircraft equipped with the safety device. [Means for solving the problem]

[0008] (1) The safety device according to the present invention is characterized by comprising: a sliding member; an actuator having a power source that generates a driving force to slide the sliding member to one side; a support portion extending from the sliding member so as to be movable together with the sliding member when in operation and supporting an injection product; a bottomed cylindrical container having a bottom portion and a side portion, which houses at least the sliding member, the actuator, the support portion, and the injection product inside, and which has one or more holes penetrating the bottom portion and the side portion, in the portion closer to the bottom portion than the support portion; and a closing portion that is breathable and waterproof and provided to close the holes.

[0009] (2) In the safety device described in (1) above, the closing portion is preferably in the form of a sheet.

[0010] (3) In the safety device described in (1) above, it is preferable that the blocking portion has a hole with a diameter of 0.1 μm to 10 μm.

[0011] (4) The aircraft according to the present invention is characterized by comprising an airframe, one of the safety devices (1) to (3) above which is coupled to the airframe, and one or more propulsion mechanisms which are coupled to the airframe and propel the airframe. [Effects of the Invention]

[0012] According to the present invention, it is possible to provide a safety device that can improve waterproof performance while suppressing a decrease in ejection performance, and an aircraft equipped with the safety device. [Brief explanation of the drawing]

[0013] [Figure 1] This is a cross-sectional view showing a safety device according to an embodiment of the present invention. [Figure 2] Figure 1 is a plan view showing the housing and closure section of the safety device. [Figure 3] Figure 1 is a front view showing an aircraft equipped with safety devices. [Figure 4] This is a cross-sectional view showing a safety device according to another embodiment of the present invention. [Modes for carrying out the invention]

[0014] <Embodiment> Hereinafter, the safety device 100 and the aircraft 30 according to the embodiment of the present invention will be described with reference to Figures 1 to 3. Figure 1 is a cross-sectional view of the safety device 100 at the position indicated by line II in Figure 2.

[0015] As shown in Figure 1, the safety device 100 comprises an actuator 1, a push-up member 15 pushed up in one direction (upward in Figure 1) by the actuator 1, an injection-molded object 16 supported and pushed up by the push-up member 15, a bottomed cylindrical container 18 that houses the actuator 1, the push-up member 15, and the injection-molded object 16, a lid 21 that closes the open end of the container 18, and a closing part 40. In this embodiment, the injection-molded object 16 is a parachute or paraglider. A closing member 60 is provided in the gap between the container 18 and the lid 21 to prevent liquid or dust from entering. Examples of this closing member 60 include any material with waterproof and dustproof functions, such as an O-ring, a hardened resin, or a foam material. As a variation of the closing member 60, a film-like material may be used to wrap at least the edge of the lid 21 and the side of the container 18.

[0016] 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 in operation; 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.

[0017] The base 2 comprises 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.

[0018] The flange portion 2B includes a plurality of holes 2a used for attachment to the container 18, a plurality of fixing holes (not shown) used for attachment to the airframe 31 of the flying object 30 described later, and an insertion port 2c used for inserting the energizing connector 22 into the lower electrode 17b of the gas generator 17, and is processed into a substantially U-shaped and substantially horseshoe-shaped (not shown). Female threads are cut on the inner wall of the hole 2a so that the bolt 28 described later can be screwed in. Also, female threads are cut on the inner wall of the fixing hole (not shown), and a bolt (not shown) is screwed from the airframe 31 side into the flying object 30 described later so that the base 2 can be fixed to the airframe 31.

[0019] The connector 22 includes a main body portion 22a that can be inserted into the substantially cylindrical member 2A through the insertion port 2c, a protruding portion (not shown) protruding from the side surface of the lower portion of the main body portion 22a, and a hole portion 22c into which the electrode 17b located in the substantially cylindrical member 2A is inserted. The protruding portion (not shown) is electrically connected to a connector (not shown) connected to an external power source via a wiring (not shown) extending in a direction perpendicular to the insertion direction of the connector 22 (when attached to the base 2, along the radial direction from the center of the base 2). Also, the main body portion 22a is provided with a hole portion 22c inside that is electrically connected to both the electrode 17b and the wiring (not shown) connected to the protruding portion (not shown).

[0020] Also, the insertion port 2c of the base 2 and the connector 22 are configured such that when attached to the base 2, they are in a state of extending along the radial direction from the center of the base 2 so that the wiring (not shown) can be arranged without blocking the holes 24a and 24b.

[0021] The piston member 10 has a main body portion 10a having a portion with an outer diameter substantially the same as the inner diameter of the cylinder body 14, a rod-shaped portion 10b connected to the main body portion 10a and 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 screw 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.

[0022] At least the upper end side of the rod-shaped portion 10b is formed with a non-circular cross-section, although not shown in the figure. Here, the non-circular shape means, for example, a polygonal shape, an elliptical shape, a star shape, or a gear shape, etc. However, as long as it is a non-circular shape, any shape is included. Also, at the lower part of the rod-shaped portion 10b, the tubular member 4 is fitted or loosely fitted in a state where one end contacts the main body portion 10a. Note that 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 the gap should be within a range that does not prevent the plastic deformation due to substantially uniform compression during the collision described later.

[0023] As shown in FIG. 1, the tubular member 4 is held by the holding member 5 at the lower part of the rod-shaped portion 10b in a state where one end contacts the main body portion 10a. Also, the tubular member 4 is made of a material that undergoes plastic deformation and has a lower tensile strength than the piston member 10 and the stopper member 23 (for example, metals such as iron, aluminum, brass, copper, etc., alloys such as stainless steel, resins, etc.) (for example, metals such as aluminum, brass, etc., alloys such as stainless steel, polyamide synthetic resins such as monomer cast nylon, nylon 6, nylon 6,6, nylon 4,6, etc.). 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 the shape may be a ring shape or a clip shape.

[0024] Also, the tubular member 4 and the inner wall portion of the cylinder 14 are separated by a predetermined distance (for example, a distance such that the plastically deformed tubular member 4 due to substantially uniform compression when colliding with the stopper member 23 does not contact the inner wall portion of the cylinder 14) so that the tubular member 4 does not contact the inner wall portion of the cylinder 14. Thus, even if the tubular member 4 collides with the stopper member 23 and undergoes plastic deformation, it can deform without being hindered by the inner wall portion of the cylinder 14, and sufficiently alleviates the impact on the piston member 10. [[ID=].]

[0025] 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.

[0026] 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.

[0027] A sealing member 11, such as an O-ring, is provided in the circumferential direction in the groove portion 10e.

[0028] 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 through holes 14a for releasing air from the space 6 to the outside when it is in operation. In Figure 1, only two through holes 14a are shown, but multiple through holes may be provided in the circumferential direction.

[0029] 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.

[0030] 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, then passes through the gap between the outer wall of the cylinder 14 and the inner wall of the bottomed cylindrical part 19, through the inside of the container 18, through the closure part 40, and released to the outside of the container 18 from the holes 24a and 24b, 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.

[0031] 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.

[0032] 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.

[0033] The bottomed cylindrical portion 19 has a bottom portion 19a that is roughly flat or roughly columnar (roughly columnar in this embodiment), a hole 51 formed on the lid portion 21 side of the bottom portion 19a, a hole 52 (second hole) with a smaller diameter than hole 51, and a hole 53 (first hole) that communicates with hole 51 via hole 52 and has a larger diameter than hole 52. Hole 51 has a diameter larger than the diameter of the head portion 50a of the bolt member 50. Hole 52 has a diameter smaller than the diameter of the head portion 50a and can guide the male threaded portion 50b of the bolt member 50 inserted from the hole 51 side to the hole 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, the hole 53 becomes a fitting portion into which one end of the rod-shaped portion 10b fits.

[0034] 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.

[0035] The support portion 20 is initially positioned spaced apart from the inner bottom surface of the container 18. The support portion 20 also has a hole 26 to reduce the effect of the 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 contact 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.

[0036] 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 arranged in multiples so as to be rotationally symmetrical with respect to the bottomed cylindrical portion 19. Holes 26 are provided between each of these movement prevention members 27. In one modification, only one movement prevention member 27 may be provided. Even in this case, multiple holes 26 are provided in the support portion 20.

[0037] As shown in Figures 1 and 2, the bottom of the container 18 is provided with a plurality of holes 24a and 24b that connect the inside and outside of the container 18, a hole 25 into which the base 2 is inserted, a hole 29a for bolt fastening, and a hole 29b that communicates with a fixing hole (not shown) for the flange portion 2B. Furthermore, the bottom of the container 18 has a recessed central portion, and this central portion and its surrounding area form at least two stepped shapes.

[0038] Each of the multiple holes 24a and 24b is provided to reduce the effect of negative pressure generated between the support portion 20 and the bottom of the container 18 during operation, thereby facilitating the pushing-up member 15. Each of the multiple holes 24a and 24b penetrates the bottom of the container 18 and is located on the bottom side of the support portion 20. The multiple holes 24a are arranged in an annular pattern at equal intervals in the circumferential direction. The multiple holes 24b are located radially outside the multiple holes 24a and are arranged in an annular pattern at equal intervals in the circumferential direction. In the radial direction, each of the multiple holes 24b is located on the outside of each of the multiple holes 24a.

[0039] The opening 25 is closed by fastening a hole 2a, provided in the flange portion 2B of the base 2 located on the outside of the bottom of the container 18, through hole 29a with a bolt 28 from the inside of the container 18. In addition, 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.

[0040] The multiple closure portions 40 are arranged in an annular pattern at equal intervals in the circumferential direction, and each of the multiple closure portions 40 is provided to close the holes 24a and 24b. Each of the multiple closure portions 40 is breathable, waterproof, and dustproof. In other words, each of the multiple closure portions 40 allows air to pass through but prevents water and dust from passing through. In this embodiment, each of the multiple closure portions 40 is in the form of a sheet and is attached to the inner surface of the bottom of the container 18 by pressure or the like. For example, each of the multiple closure portions 40 is a breathable membrane having multiple holes (pores) with a diameter of 0.1 μm to 10 μm, preferably 2 to 5 μm. When the push-up member 15 moves rapidly inside the container 18, negative pressure is generated in the region between the push-up member 15 and the bottom surface of the container 18. Therefore, it becomes difficult to move the push-up member 15. Therefore, by providing the holes 24a and 24b, the negative pressure phenomenon can be reduced, and the push-up member 15 can be moved smoothly. However, there is a risk that liquid, dust, etc. may enter the inside of the container 18 through the holes 24a and 24b. For this reason, by providing a closure section 40 that is breathable, waterproof, and dustproof, the effect of reducing the negative pressure phenomenon by providing the holes 24a and 24b can be maintained, while preventing the rise in pressure and temperature caused by sealing the container 18 (for example, changes in pressure and temperature inside the container 18 due to changes in altitude can be suppressed). In addition, the entry of liquid, dust, etc. into the inside of the container 18 through the holes 24a and 24b can be suppressed, and deterioration and damage to the injection material 16 and various devices such as sensors (not shown) inside the container 18 can be suppressed.

[0041] The injected 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 injected material 16 is also folded so that its outer surface does not come into contact with the inside of the containment container 18. The injected 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 holes 26) or to the body 31 of the aircraft 30, which will be described later. As one modification, the injected material 16 may be folded so that its outer surface comes into contact with the inside of the containment container 18.

[0042] 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.

[0043] 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.

[0044] In the configuration described above, when the gas generator 17 is activated when a flying object 30, for example, equipped with the safety device 100, falls, the piston member 10 is propelled upward within the cylinder 14 by the pressure of the gas generated by the activation, starting from the initial state shown in Figure 1. 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 container 18. This causes the lid 21 to detach, the open end of the container 18 to open, and the ejected material 16 to be ejected outward from inside the container 18 (upward in the plane of the paper in Figure 1). At this time, negative pressure is generated in the region between the support portion 20 of the push-up member 15 and the bottom surface of the container 18, and outside air flows into the container 18 through the holes 24a, 24b and the closure portion 40. Subsequently, the piston member 10 and the tubular member 4 move upward, but the tubular member 4 collides with the stopper member 23 and stops. Furthermore, if the projectile 16 is a parachute or paraglider, the projectile 16 is deployed after being ejected from the containment 18.

[0045] As shown in Figure 3, the safety device 100 is connected and fixed to the aircraft body 31 of the aircraft 30 from the aircraft body 31 side via fixing holes (not shown) of the base 2 using bolts (not shown). At this time, the base 2 connects the housing 18 and the aircraft body 31 in a position that does not block the holes 24a and 24b. Therefore, the aircraft 30 comprises an aircraft body 31, a 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 to propel the aircraft body 31, and a plurality of legs 33 provided on the lower part of the aircraft body 31.

[0046] 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.

[0047] In the above configuration, there are holes 24a and 24b that connect the inside and outside of the container 18, and a sealing part 40 that closes the holes 24a and 24b, providing both ventilation and waterproofing. Therefore, according to this embodiment, even during operation, a decrease in injection performance that would occur if the container 18 did not have holes 24a and 24b can be prevented. Furthermore, according to this embodiment, since the holes 24a and 24b are closed by the sealing part 40 in the initial state, the waterproofing performance can be improved before operation compared to when the sealing part 40 is not present, and premature deterioration or damage of the injection material 16 can be prevented.

[0048] Furthermore, an aircraft 30 equipped with a safety device 100 having the configuration described above can be obtained.

[0049] As described above, the safety device 100 in the embodiment of the present invention comprises a piston member 10, an actuator 1 having a gas generator 17 that generates a driving force to slide the piston member 10 to one side, a support portion 20 that extends from the piston member 10 so as to be movable together with the piston member 10 when in operation and supports the injectable material 16, a bottomed cylindrical container 18 having a bottom and sides, which houses at least the piston member 10, the actuator 1, the support portion 20, and the injectable material 16 inside, and which has one or more holes 24a, 24b penetrating the bottom portion of the bottom and the sides, which are located on the bottom side of the support portion 20 (the bottom portion in this embodiment), and a closing portion 40 that is breathable and waterproof and is provided to close the holes 24a, 24b.

[0050] According to this, since the closure part 40 is waterproof, the waterproof performance can be improved by the closure part 40 before operation. Also, since the closure part 40 is breathable, outside air can be allowed to flow into the inside of the container 18 by passing through the closure part 40 during operation, thereby suppressing a decrease in injection performance. In this way, it is possible to improve waterproof performance while suppressing a decrease in injection performance.

[0051] Furthermore, in the safety device 100 according to the embodiment of the present invention, the blocking portion 40 is in the form of a sheet.

[0052] According to this, it is possible to suppress the bulkiness of the occlusion section 40 while suppressing a decrease in injection performance and improving waterproof performance.

[0053] Furthermore, the aircraft 30 in the embodiment of the present invention comprises an airframe 31, a safety device 100 coupled to the airframe 31, and one or more propulsion mechanisms 32 coupled to the airframe 31 for propelling the airframe 31.

[0054] According to this, it will have the same effects as the safety device 100 described above.

[0055] <Other Embodiments> 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 further included.

[0056] In the above embodiment, instead of, or together with, the hole provided at the bottom of the container, one or more holes for reducing negative pressure may be provided on the side of the container, on the bottom side of the support portion that supports the injection material. Furthermore, the holes provided on the side may be closed by the closure portion shown in the above embodiment, so that outside air passes through the closure portion and flows into the inside of the container during operation.

[0057] Furthermore, for example, in the safety device 200 shown in Figure 4, the bottom of the container 118 may be provided with a hole 124a, similar to the holes 24a and 24b in the above embodiment, and a closing part 140 that closes the hole 124a, similar to the closing part 40 in the above embodiment. In addition, a closing part 140 that closes one or more holes 118a formed on the side of the container 118 may be provided. Note that symbols with the same last two digits as those in the above embodiment are the same and their explanations may be omitted. Also, parts that are not specifically explained are the same as in the above embodiment and their explanations may be omitted.

[0058] Furthermore, although the closure portion 40 was in the form of a sheet in the above embodiment, the closure portion may be in the form of a plate or the like. Also, the closure portion 40 may be composed of one sheet or multiple sheets. The same applies to the other embodiments described above.

[0059] Furthermore, in the above embodiment, the closing portion 40 is attached to the inner surface of the bottom of the container 18, but the closing portion 40 may also be attached to the outer surface of the bottom of the container 18. Alternatively, the closing portion may be provided inside the holes 24a and 24b so as to fill the holes 24a and 24b. The same applies to the other embodiments described above.

[0060] Furthermore, in the above embodiment, a portion of the base 2 was configured to be located outside the housing 18, but the entire base 2 may be configured to be located inside the housing 18.

[0061] Furthermore, although a gas generator was used as the power source in the above embodiment, the configuration is not limited as long as it is capable of providing the sliding member with the driving force necessary for the sliding member to propel itself within the cylinder. For example, an elastic body such as a spring, or a system using pressure from a gas cylinder, may be used. The same applies to the other embodiments described above.

[0062] 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. The same applies to the other embodiments described above.

[0063] Furthermore, in the above embodiment, 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. The same applies to the other embodiments described above.

[0064] 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 driving the motor, the control lines can be wound up or unwound, thereby pulling or releasing the lift-generating member as appropriate. The same applies to the other embodiments described above.

[0065] Furthermore, the projectile may be a pilot chute, and the safety device may include a parachute connected to the pilot chute. In this case, for example, the safety device may include a separate housing for the parachute in addition to the housing for the pilot chute.

[0066] Alternatively, the aircraft may be equipped with a safety device capable of launching a net instead of a parachute or paraglider. This allows the aircraft to hook onto a hook or protrusion by launching the net at the right time, thereby preventing the aircraft from falling to the ground. Furthermore, instead of a parachute or paraglider, the aircraft may be capable of launching medical supplies, cargo, etc.

[0067] 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.

[0068] 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.

[0069] 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.

[0070] 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.

[0071] 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 to danger.

[0072] 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.

[0073] 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.

[0074] 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.

[0075] 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.

[0076] 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.

[0077] 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]

[0078] 1 Actuator 2 bases 2A Approximately cylindrical member 2B Flange section 2a,13,24a,24b,25,26,51,52,53,118a,124a Hole 2c insertion slot 3. Cylindrical member 4 Tubular member 5. Retaining member 6 Space 10 Piston member 10a Main body 10b Rod-shaped part 10c,22c hole 10d Female thread section 10e,23a,23b Groove 11,12 Sealing member 14 cylinders 14a Through hole 15,115 Push-up members 16,116 Projectiles 17,117 Gas generators 17a Cup body 17b Electrode 18,118 containers 19,119 Bottomed cylindrical part 19a bottom 20,120 Support part 21,121 Lid 22 connectors 22a Main body 23 Stopper member 27 Movement prevention member 28 volts 29a,29b hole 30 flying objects 31 aircraft 32 Propulsion mechanism 33 Legs 40,140 Occlusion 50 Bolt Members 50a Head section 50b Male threaded section 53a Insertion opening 60 Closure member 100,200 Safety equipment

Claims

1. Sliding member and An actuator having a power source that generates a driving force to slide the sliding member to one side, A support portion is provided that extends from the sliding member so as to be movable together with the sliding member during operation, and supports the injection material. A bottomed cylindrical container having a bottom and sides, which houses at least the sliding member, the actuator, the support part, and the injection material inside, and which has one or more holes penetrating the bottom and sides, in the portion of the bottom that is closer to the support part. A closure portion that is breathable and waterproof and is provided to close the hole, A safety device characterized by being equipped with the following features.

2. The safety device according to claim 1, characterized in that the blocking portion is in the form of a sheet.

3. The safety device according to claim 1, characterized in that the occluded portion has a hole with a diameter of 0.1 μm to 10 μm.

4. The aircraft and, A safety device according to any one of claims 1 to 3, which is coupled to the aircraft body, An aircraft characterized by comprising one or more propulsion mechanisms coupled to the aforementioned aircraft and propelling the aircraft.

Images