Safety devices, and aircraft equipped with safety devices

Abstract

The present invention provides a safety device that can prevent the ejection of projectiles from being obstructed by the side wall, and an aircraft equipped with the safety device. [Solution] The safety device 100 comprises a container 10 having a bottom 11, a top 12 facing the bottom 11, and a side wall 13 that is divided into multiple parts and supported by the top 12 such that each of the multiple divided pieces 13a, 13b can rotate outward; a restricting unit that restricts each of the multiple divided pieces 13a, 13b from rotating relative to the top 12 when the side wall 13 is attached to the bottom 11; an injection material contained in the container 10; and an actuator that, when activated, removes the side wall 13 from the bottom 11 together with the top 12 and ejects the injection material. When the side wall 13 is removed from the bottom 11 by the actuator, the restriction by the restricting unit is released, and each of the multiple divided pieces 13a, 13b becomes rotatable relative to the top 12.

Description

Technical Field

[0006] , , , , , ,

[0005] ,

[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, for example, by simultaneously rotating a plurality of rotors in a balanced manner, and ascending and descending are performed by increasing and decreasing the rotational speed of the rotors, and forward and backward movement can be achieved by tilting the aircraft through increasing and decreasing the rotational speed of the rotors. Such an aircraft is not only used for disaster relief activities, cargo transportation, landscape photography, etc., but is also assumed to carry passengers, and is expected to be more widely used worldwide in the future.

[0003] On the other hand, the risk of a falling accident of the above-mentioned aircraft is regarded as dangerous, etc., which has hindered the spread of the aircraft. In order 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 payload deployment mechanism provided with a hinge mechanism. The hinge mechanism can enable the payload to separate from the payload deployment mechanism without contacting the payload deployment mechanism.

Prior Art Documents

Patent Documents

[0005]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0006] Incidentally, when an injectable material is contained in a container having a bottom, a top, and side walls, and then ejected from the container, the ejection of the injectable material may be obstructed by the side walls. Therefore, it is desirable to suppress the obstruction of the ejectable material by the side walls.

[0007] Therefore, the present invention aims to provide a safety device that can prevent the ejection of an ejected object from being obstructed by the side wall, and an aircraft equipped with the safety device. [Means for solving the problem]

[0008] (1) The safety device according to the present invention comprises a container having a bottom, a ceiling facing the bottom, and a side wall divided into a plurality of segmented pieces; a restricting unit capable of restricting each of the plurality of segmented pieces from rotating outwards from the container, while being supported by any part of the container other than its own segmented piece, so that each of the plurality of segmented pieces can rotate outwards from any part of the container other than its own segmented piece; an injection product to be contained in the container; and an injection unit that, when activated, ejects the injection product together with the ceiling. The safety device is characterized in that when the ceiling is ejected by the injection unit, the restriction by the restricting unit is released, and each of the plurality of segmented pieces becomes rotatable relative to the container.

[0009] (2) In the safety device described in (1) above, the restricting portion is provided at the bottom and restricts each of the plurality of segmented pieces from rotating outward relative to the ceiling portion of the container in the initial state in which the side wall portion is attached to the bottom, and it is preferable that the side wall portion is removed from the bottom when the injection portion is activated.

[0010] (3) From another perspective, in the safety device described in (1) above, the restricting portion is provided on the ceiling and restricts each of the plurality of segmented pieces from rotating outward relative to the bottom of the container in the initial state in which the side wall portion is attached to the ceiling portion, and the side wall portion may be removed from the ceiling portion when the injection portion is activated.

[0011] (4) In the safety devices described in (1) to (3) above, it is preferable that each of the plurality of segmented pieces is supported on the ceiling by a hinge structure so that it can rotate outwards from the container.

[0012] (5) In the safety devices described in (1) to (3) above, it is preferable to have a trigger device for an aircraft that has an activation unit for activating the ejection unit in at least one of the following cases: when the aircraft is determined to be in an abnormal state, and when the operator of the aircraft gives an instruction to activate the ejection unit.

[0013] (6) In the safety devices described in (1) to (3) above, it is preferable that the ejected material is a pilot chute and that a parachute connected to the pilot chute is provided.

[0014] (7) The aircraft according to the present invention is characterized by comprising an airframe, any of the safety devices described in (1) to (3) above which are coupled to the airframe, and one or more propulsion mechanisms which are coupled to the airframe and propel the airframe. [Effects of the Invention]

[0015] According to the present invention, it is possible to provide a safety device that can prevent the ejection of an ejected object from being obstructed by the side wall, and an aircraft equipped with the safety device. [Brief explanation of the drawing]

[0016] [Figure 1] This is a perspective view showing a safety device according to a first embodiment of the present invention. [Figure 2] It is a plan view showing the safety device of FIG. 1. [Figure 3] It is a cross-sectional view taken along line III-III of FIG. 2. [Figure 4] It is a cross-sectional view taken along line IV-IV of FIG. 2. [Figure 5] It is an end view taken along line V-V of FIG. 3. [Figure 6] It is a perspective view showing the state where the side wall portion of the safety device of FIG. 1 is rotated. [Figure 7] It is a block diagram showing the functional configuration of the safety device of FIG. 1. [Figure 8] It is a front view showing an aircraft equipped with the safety device of FIG. 1. [Figure 9] It is a perspective view showing the safety device according to the second embodiment of the present invention. [Figure 10] It is a perspective view showing the state where the side wall portion according to a modification of the present invention is rotated.

Mode for Carrying Out the Invention

[0017] <First Embodiment> Hereinafter, the safety device 100 and the aircraft 1 according to the first embodiment of the present invention will be described with reference to FIGS. 1 to 8.

[0018] First, the safety device 100 will be described with reference to FIGS. 1 to 7. As shown in FIGS. 1 to 5, the safety device 100 includes a container 10, a regulating unit 20, a projectile 30, an actuator 40, a bolt 60, and a harness 70. In FIGS. 3 and 4, the projectile 30 is virtually shown by a two-dot chain line. Also, in FIG. 5, the illustration of the projectile 30 is omitted.

[0019] The container 10 houses the projectile 30. The container 10 has a bottom 11, a ceiling 12, a side wall 13, and a support member 14.

[0020] The bottom 11 has a bottom plate portion 11a and a wall portion 11b.

[0021] The injection-molded material 30 is placed on the bottom plate portion 11a. The bottom plate portion 11a is plate-shaped with the sliding direction of the piston member 41 as the thickness direction. In the following, the sliding direction of the piston member 41 may be simply referred to as the sliding direction. When viewed from the sliding direction, the bottom plate portion 11a is circular. The bottom plate portion 11a has a hole portion 11c and a hole portion 11d.

[0022] The hole 11c is formed in the center of the bottom plate 11a and penetrates the bottom plate 11a in the sliding direction. The actuator 40 is inserted through the hole 11c.

[0023] Multiple holes 11d are provided, and each of the multiple holes 11d is formed outside the center of the bottom plate portion 11a. The multiple holes 11d are arranged around the hole 11c. Each of the multiple holes 11d penetrates the bottom plate portion 11a in the sliding direction. A bolt 60 for fixing the housing 10 and the actuator 40 is inserted through each of the multiple holes 11d.

[0024] The wall portion 11b has an annular portion 11e, a protruding portion 11f, and a hole portion 11g.

[0025] The annular portion 11e protrudes from one side of the main surface of the base plate portion 11a (the side indicated by arrow X in Figure 3, etc.). This side is the side on which the piston member 41 slides due to the driving force generated by the gas generator 49. When viewed from the sliding direction, the annular portion 11e is annular, and the center of the annular portion 11e coincides with the center of the base plate portion 11a. The annular portion 11e is positioned slightly inward from the outer circumference of the base plate portion 11a.

[0026] Multiple protrusions 11f are provided, and each of the multiple protrusions 11f protrudes inward from the inner circumference of the annular portion 11e. The multiple protrusions 11f are arranged at equal intervals in the circumferential direction of the annular portion 11e.

[0027] Multiple holes 11g are provided, and each of the multiple holes 11g corresponds to a multiple protrusion 11f. Each of the multiple holes 11g penetrates the annular portion 11e and the corresponding protrusion 11f in the radial direction of the annular portion 11e.

[0028] The ceiling portion 12 faces the bottom portion 11. The ceiling portion 12 has a top plate portion 12a and a cylindrical portion 12b.

[0029] The top plate portion 12a is located on one side of the piston member 41. The top plate portion 12a is plate-shaped with its sliding direction as the thickness direction. When viewed from the sliding direction, the top plate portion 12a is approximately circular. The top plate portion 12a has notches 12c and 12d, a chamfered portion 12e, and a hole 12f.

[0030] The notches 12c and 12d are provided so as to cut out the outer periphery of the top plate portion 12a. The notches 12c and 12d are provided from the main surface on one side of the top plate portion 12a to the other side (the side indicated by arrow Y in Figure 3, etc.). The notches 12c and 12d are provided at equal intervals in the circumferential direction.

[0031] The chamfered portion 12e is provided to chamfer the corner where the other main surface of the top plate portion 12a, the outer circumferential surface of the top plate portion 12a, and the notch portion 12c intersect, and is provided so that the divided piece 13a of the side wall portion 13 can rotate outward. Similarly, the chamfered portion 12e is provided to chamfer the corner where the other main surface of the top plate portion 12a, the outer circumferential surface of the top plate portion 12a, and the notch portion 12d intersect, and is provided so that the divided piece 13b of the side wall portion 13 can rotate outward.

[0032] Multiple holes 12f are provided, and each of the multiple holes 12f penetrates the top plate portion 12a in the sliding direction. A string-like connecting member (not shown) that connects the top plate portion 12a and the injection molded product 30 is inserted through the multiple holes 12f.

[0033] The cylindrical portion 12b extends from the other main surface of the top plate portion 12a to the other side and opens to the other side. An actuator 40 is positioned inside the cylindrical portion 12b.

[0034] The side wall portion 13 is divided into multiple sections, and has multiple divided pieces 13a, 13b. Each of the multiple divided pieces 13a, 13b is supported by the top plate portion 12a so as to be able to rotate outward. In this embodiment, each of the multiple divided pieces 13a, 13b is supported by the top plate portion 12a so as to be able to rotate outward by a hinge structure. The side wall portion 13 is substantially cylindrical when the multiple divided pieces 13a, 13b are not rotated outward (as shown in Figure 1, etc.).

[0035] Each of the multiple segmented pieces 13a and 13b is formed in a substantially arc shape along the outer circumference of the top plate portion 12a when not rotated outward. The multiple segmented pieces 13a and 13b are formed to fit with the annular portion 11e when not rotated outward. The multiple segmented pieces 13a and 13b are formed so that their ends fit together when not rotated outward (see Figure 5). Each of the multiple segmented pieces 13a and 13b has a protruding portion 13c and a hole portion 13d.

[0036] The protruding portion 13c of the segmented piece 13a protrudes to one side and is inserted into the notch 12c when the segmented piece 13a is not rotated outward. The protruding portion 13c of the segmented piece 13b protrudes to one side and is inserted into the notch 12d when the segmented piece 13b is not rotated outward.

[0037] The hole 13d of the divided piece 13a is provided so as to overlap radially with one of the holes 11g when the divided piece 13a is not rotated outward. The hole 13d of the divided piece 13b is provided so as to overlap radially with the other hole 11g when the divided piece 13b is not rotated outward.

[0038] The support member 14 is a member that allows the top plate portion 12a to rotatably support multiple divided pieces 13a, 13b. The support member 14 has shafts 14a, 14b.

[0039] The shaft 14a is inserted through the projection 13c of the segmented piece 13a in a direction perpendicular to the sliding direction, and both ends of the shaft 14a are inserted into and supported by the top plate 12a. The segmented piece 13a is supported by the top plate 12a so as to be able to rotate outward by a hinge structure formed by the shaft 14a, the projection 13c, and the top plate 12a. The shaft 14b is inserted through the projection 13c of the segmented piece 13b in a direction perpendicular to the sliding direction, and both ends of the shaft 14b are inserted into and supported by the top plate 12a. The segmented piece 13b is supported by the top plate 12a so as to be able to rotate outward by a hinge structure formed by the shaft 14b, the projection 13c, and the top plate 12a. The hinge structure may also be of a type such as a square hinge, finial hinge, free hinge, piano hinge, hinge latch, curved hinge, cabinet hinge, concealed hinge, slide hinge, angle hinge (rabbit hinge), glass hinge, stay, removable hinge, flag hinge, spring hinge, French hinge (knuckle hinge), release hinge, flush hinge, torque hinge, drop hinge (sewing machine hinge), clean hinge, pivot hinge, auto hinge hinge, or antique hinge.

[0040] The restricting section 20 restricts each of the multiple segmented pieces 13a, 13b from rotating relative to the ceiling section 12 when the side wall section 13 is attached to the bottom section 11. The restricting section 20 has pins 21, 22.

[0041] Pin 21 is inserted into holes 13d and 11g of segment 13a so as not to come out. Pin 22 is inserted into holes 13d and 11g of segment 13b so as not to come out. With pins 21 and 22 inserted in this way, the side wall 13 is attached to the bottom 11. In this state, each of the multiple segment pieces 13a and 13b cannot rotate relative to the top 12. When the actuator 40 is activated and pushes the top 12 to one side, pins 21 and 22 break, and the side wall 13 is removed from the bottom 11 along with the top 12. Once the side wall 13 is removed from the bottom 11, each of the multiple segment pieces 13a and 13b becomes rotatable relative to the top 12. Furthermore, when the actuator 40 is activated and pushes the ceiling portion 12 to one side, each of the multiple segmented pieces 13a and 13b may break through the hole 13d, thereby removing the side wall portion 13 from the bottom portion 11 along with the ceiling portion 12.

[0042] The projectile 30 is housed in the containment 10. Specifically, the projectile 30 is housed outside the cylindrical portion 12b. The projectile 30 is ejected from the containment 10 when the side wall portion 13 is detached from the bottom portion 11 along with the top portion 12. For example, if the side wall portion 13 is detached from the bottom portion 11 along with the top portion 12 while the aircraft 1 (described later) to which the safety device 100 is attached is falling, the projectile 30 will be exposed to the outside and will be ejected by wind pressure or by being pulled out by a string-like connecting member (not shown) connected to the top portion 12. Alternatively, a support member (a member with an overall shape similar to a "hat" among hats) may be provided, extending from the piston member 41 to support the projectile 30. By sliding the piston member 41 to one side, the side wall portion 13 together with the top portion 12 is removed from the bottom portion 11, and the support member is moved to one side. By moving the support member to one side, the projectile 30 supported by the support member may be ejected. In this embodiment, the projectile 30 is a parachute or a paraglider. For example, the parachute is a float parachute. A float parachute is a parachute with a float (lifebuoy). The projectile 30 may also be a net for capture or restraint, a fire extinguishing agent, a life-saving device, or a medicine, etc.

[0043] Furthermore, the ejected material 30 includes the following parachutes: "Cross", "Float Parachute", "Flat Circular", "Conical", "Biconical", "Triconical", "Extended Skirt", "Hemispherical", "Guide Surface", "Annular", "Flat Ribbon", "Conical Ribbon", "Ribbon", "Ring Slot", "Ring Sail", "Disc-Gap-Band", "Rotafoil", "Vortex Ring", and "Sandia RFD". It may also be called RFD, Paracommander, Parawing, Parafoil, Sailwing, Volplane, or Ballute, etc.

[0044] Actuator 40 is an example of an injection unit. Actuator 40 includes a piston member 41, a tubular member 42, a holding member 43, a sealing member 44, a cylinder 45, a stopper member 46, a sealing member 47, a base 48 (squib holder), a gas generator 49 (micro gas generator, etc.), and a cylindrical member 50.

[0045] The piston member 41 is a sliding member. The cylinder 45 houses the piston member 41. The base 48 is attached to the bottom 11 inside the housing 10 via a central hole 11c, to which one end of the cylinder 45 is crimped and fixed. The gas generator 49 is a power source that moves the piston member 41 inside the cylinder 45.

[0046] The base 48 includes a substantially cylindrical member 48a that holds a gas generator 49, which generates power to slide the piston member 41, on the cylinder 45 side, and a flange portion 48b provided on the side of the substantially cylindrical member 48a opposite to the cylinder 45 side.

[0047] The flange portion 48b is machined into a roughly U-shaped, roughly horseshoe shape (not shown), and includes a plurality of holes 48c used for attachment to the housing 10, a plurality of fixing holes (not shown) used for attachment to the airframe 2 of the aircraft 1 described later, and an insertion opening 48d used for inserting a power supply connector 71 into the electrode 49b at the bottom of the gas generator 49. The inner wall of the holes 48c is threaded, so that bolts 60 described later can be screwed in. The inner wall of the fixing holes (not shown) is also threaded, so that bolts (not shown) can be screwed into the aircraft 1 from the airframe 2 side, so that the base 48 can be fixed to the airframe 2.

[0048] The connector 71 comprises a main body 71a that can be inserted into a substantially cylindrical member 48a via an insertion opening 48d, a projection (not shown) protruding from the side of the lower part of the main body 71a, and a hole 71b into which an electrode 49b located inside the substantially cylindrical member 48a is fitted. The projection (not shown) is electrically connected to a connector 73 connected to an external power source via wiring 72 that extends in a direction perpendicular to the insertion direction of the connector 71 (radially from the center of the base 48 when mounted on the base 48). The main body 71a also has a hole 71b inside that is electrically connected to both the electrode 49b and the wiring 72 connected to the projection (not shown).

[0049] Furthermore, the insertion port 48d of the base 48 and the connector 71 are configured such that, when attached to the base 48, they extend radially from the center of the base 48.

[0050] The piston member 41 has a main body portion 41a having an outer diameter approximately the same as the inner diameter of the cylinder 45, a rod-shaped portion 41b connected to the main body portion 41a, extending upward and having a smaller diameter than the main body portion 41a, a hole portion 41c provided inside the main body portion 41a and the rod-shaped portion 41b, a hole portion 41d provided at the upper end of the rod-shaped portion 41b, and a groove portion 41e provided in the circumferential direction of the main body portion 41a.

[0051] At least the upper end of the rod-shaped portion 41b has a non-circular cross-section (see Figure 5). Here, a non-circular shape includes, for example, a polygonal shape, an elliptical shape, a star shape, or a gear shape, but any shape that is non-circular is included. In addition, a tubular member 42 is fitted or loosely fitted to the lower part of the rod-shaped portion 41b with one end in contact with the main body portion 41a. There may be a gap between the inner wall of the tubular member 42 and the outer wall of the rod-shaped portion 41b, but this gap should not hinder the plastic deformation due to substantially uniform compression during impact, which will be described later.

[0052] The tubular member 42 is held by the holding member 43 at the lower part of the rod-shaped portion 41b, with one end in contact with the main body portion 41a. The tubular member 42 is made of a material that is plastically deformable and has a tensile strength lower than that of the piston member 41 and the stopper member 46 described later (for example, metals such as iron, aluminum, brass, copper, alloys such as stainless steel, resins, etc.). Here, the holding member 43 may be an elastic material such as rubber, or it may be made of the same material as the tubular member 42, and its shape may be ring-shaped or clip-shaped.

[0053] Furthermore, to prevent the tubular member 42 from contacting the inner wall of the cylinder 45, the tubular member 42 and the inner wall of the cylinder 45 are separated by a predetermined distance or more (for example, a distance at which the tubular member 42, which has undergone plastic deformation due to substantially uniform compression upon impact with the stopper member 46, will not come into contact with the inner wall of the cylinder 45). As a result, even if the tubular member 42 undergoes plastic deformation upon impact with the stopper member 46, it will deform without being hindered by the inner wall of the cylinder 45, and the impact on the piston member 41 will be sufficiently mitigated.

[0054] The hole 41c is formed along the central axis from the lower end of the main body 41a to partway along the rod-shaped portion 41b. As a result, the piston member 41 is lighter than when the hole 41c is not formed.

[0055] The hole 41d is formed along the central axis from the tip of the rod-shaped portion 41b up to a certain point.

[0056] A sealing member 44, such as an O-ring, is provided in the circumferential direction in the groove portion 41e.

[0057] A substantially cylindrical stopper member 46 is provided at the top of the cylinder 45, positioned to surround a portion of the rod-shaped portion 41b of the piston member 41. That is, the rod-shaped portion 41b is inserted through the hole 46a of the stopper member 46. The cylinder 45 is also provided with through holes 45b to release air from the space 45a to the outside when it is in operation. Although only two through holes 45b are provided, multiple through holes may be provided in the circumferential direction.

[0058] The stopper member 46 restricts the movement of the tubular member 42 to the cylinder 45 and has a groove 46b along its outer circumference and a groove 46c along its inner circumference. The groove 46b is used to crimp and fix the other end of the cylinder 45 to the stopper member 46. A sealing member 47, such as an O-ring, is provided in the circumferential direction of the groove 46c.

[0059] The cylinder 45 may be made of a material and its outer wall thickness may be appropriately adjusted so that it can plastically deform radially in the event that the piston member 41 of the actuator 40 becomes immobile for any reason, and the initial combustion volume of the actuator 40 is reduced, causing the gunpowder to burn and generating a combustion pressure exceeding the pressure resistance value of the cylinder 45 (an abnormal situation). Examples of materials that make up the cylinder 45 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 45 plastically deforms radially, reducing (mitigating) the sealing performance of the sealing member 44, such as an O-ring, and creating a gap between the sealing member 44 and the inner wall of the cylinder 45 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 45 from the through-hole 45b, then through the gap between the outer wall of the cylinder 45 and the inner wall of the cylindrical portion 12b, passing through the inside of the containment 10, and the gas pressure causes the sealing portion (not shown) to break, and the gas is released to the outside of the containment 10 from the hole (not shown), thus preventing the cylinder 45 from breaking (fail-safe function). In the case of this fail-safe function, a space (gap) is provided between the outer wall of the cylinder 45 and the inner wall of the cylindrical portion 12b that allows the cylinder 45 to undergo sufficient plastic deformation in the radial direction.

[0060] The gas generator 49 is positioned below the main body 41a of the piston member 41, pressed into the lower open end of the cylinder 45. A cylindrical member 50 is provided around the cup body 49a of the gas generator 49 to form a predetermined distance from the piston member 41. The gas generator 49 is positioned on the other side of the piston member 41, inserted through the other opening of the cylinder 45. The gas generator 49 may use only an igniter, or a gas generator equipped with both an igniter and a gas generating agent may be used. 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, a heating element made of a gas generating agent composition or a thermite composition may be provided in the gas generator. The gas generator 49 is a micro gas generator, etc. The gas generator 49 has a cup body 49a and a plurality of electrodes 49b.

[0061] An igniter is located inside the cup-shaped body 49a. Additionally, a gas generating agent, a gas cylinder, and / or a heating element may be appropriately placed inside the cup-shaped body 49a. The electrode 49b is electrically connected to the igniter located inside the cup-shaped body 49a.

[0062] The bolt 60 is a component used to fix the housing 10 and the actuator 40. The bolt 60 is inserted through the hole 11d from the inside of the housing 10 and screwed into the hole 48c. By tightening the bolt 60, the housing 10 and the actuator 40 are fixed together.

[0063] The harness 70 is a component for electrically connecting the gas generator 49 and the trigger device 80 (described later). The harness 70 has a connector 71, wiring 72, and connector 73.

[0064] Connector 71 is located on the other side of the gas generator 49 and is connected to electrode 49b. Wiring 72 is connected to connector 71 and connector 73. Connector 73 is connected to trigger device 80. This allows a signal from trigger device 80 to be supplied to the gas generator 49, causing the gas generator 49 to operate.

[0065] As shown in Figure 6, when the restricting portion 20 is not in place, each of the multiple segmented pieces 13a and 13b is rotatable outward. Segmented piece 13a is restricted from rotating outward by contacting the chamfered portion 12e provided on the notch portion 12c. Similarly, segmented piece 13b is restricted from rotating outward by contacting the chamfered portion 12e provided on the notch portion 12d.

[0066] When the actuator 40 is activated, the side wall section 13 is removed from the bottom section 11 along with the ceiling section 12, and the ejected material 30 is ejected, the ceiling section 12 and side wall section 13 separate from the bottom section 11, are launched upward, and fall. For example, if the ejected material 30 is a parachute, the parachute is packed into the container 10 so as to be pushed in. In this state, when the actuator 40 is activated and the pins 21 and 22 are broken by ejecting the ceiling section 12 and side wall section 13, each of the multiple segmented pieces 13a and 13b after the ejection will rotate outward due to the parachute's self-restoring force (the force that causes the parachute pushed into the container 30 to naturally try to unfold), resulting in the state shown in Figure 6. This separates the injection material 30 from the side wall portion 13, suppressing sliding resistance and other interference from the side wall portion 13. This prevents the injection material 30 from getting stuck in the side wall portion 13 and prevents the side wall portion 13 from hindering the injection of the injection material 30. In addition, as each of the multiple segmented pieces 13a and 13b rotates outward, air resistance increases, which suppresses the speed of the injected ceiling portion 12 and side wall portion 13 from becoming too fast. Therefore, the difference between the speed of the ceiling portion 12 and side wall portion 13 after separation from the injection material 30 and the speed of the injection material 30 after separation (after deployment begins) can be made smaller, thus suppressing the increased pulling force exerted by the ceiling portion 12 and side wall portion 13 on the injection material 30 after separation. Furthermore, by changing the angle of the chamfered portion 12e, the maximum angle by which the divided pieces 13a and 13b rotate can be changed. By appropriately setting the maximum angle by which the divided pieces 13a and 13b rotate (for example, to 45 degrees), the air resistance of the injected material 30 immediately after the ceiling portion 12 and side wall portion 13 are ejected can be reduced compared to conventional methods, thereby improving the ejectability of the injected material 30 (its ability to be ejected further away from the container 10) compared to conventional methods.

[0067] Here, we describe the results of actually measuring the tensile load applied to the connecting member (here, a string) that connects the parachute to the safety device or the main body of the aircraft when the actuator is activated and the projectile is launched, using a safety device with the same configuration as in this embodiment. The measured tensile load applied to the connecting member was approximately 275 [N]. For example, if the load capacity of the string used for the connecting member is 1000 [N], the tensile load applied to the connecting member during launch will naturally be less than the load capacity of the connecting member. Furthermore, when a similar experiment was conducted on a safety device (comparative example) in which the containment is a single cylindrical structure that is not divided as in this embodiment, the tensile load applied to the connecting member (here, a string) during launch was 730 [N]. From these experimental results, the following can be considered. That is, although the safety device of the comparative example makes it easier to achieve a long launch distance for the projectile, the aforementioned tensile load is relatively high, and the projectile is more likely to be subjected to stress. For example, if the projectile is a parachute, it becomes necessary to use a parachute that can withstand the load (for example, one with high strength in the fabric that makes up the parachute; generally, the higher the strength, the heavier the parachute tends to be) to prevent it from tearing. In contrast, in the safety device with the same configuration as in this embodiment, the segmented pieces that make up the containment are configured to rotate and open, so the projected area is larger than that of the containment structure of the safety device of the comparative example, and the air resistance during ejection increases. As a result, the projectile travels further, but the force of the ejection is not made too strong, so it is possible to control the parachute so as not to pull it too hard. Therefore, it was found that the safety device with the same configuration as in this embodiment not only makes it easier to achieve a long projectile travel distance, similar to the safety device of the comparative example, but also allows for a lower tensile load compared to the containment of the safety device of the comparative example. In other words, for example, if the projectile is a parachute, the safety device with the same configuration as in this embodiment can reduce the load on the parachute during ejection relatively small, so the parachute used in the safety device with the same configuration as in this embodiment does not need to be as strong as the parachute in the safety device of the comparative example.The tensile load applied to the connecting member after injection was measured by fixing the load sensor and the bottom of the container in a vise, attaching one end of the connecting member to the ceiling, and attaching the other end of the connecting member to the load sensor.

[0068] As shown in Figure 7, the safety device 100 includes a trigger device 80. For example, the trigger device 80 is housed in a casing (not shown) and mounted on the aircraft 1. The trigger device 80 has a control unit 81, a determination unit 82, a storage unit 83, and a notification unit 84. The control unit 81 has a CPU, ROM, RAM, etc. The determination unit 82 determines whether the aircraft 1 is in an abnormal state based on signals received from a detection unit 90 that detects the state of the aircraft 1 (malfunction, uncontrollable, flight status (flight attitude, speed, angular velocity, altitude, attitude angle, etc.), distance to obstacles, position information, etc.). The trigger device 80 uses the CPU to execute various programs (signal transmission program, signal reception program, etc.) and can automatically transmit command signals, operation signals, etc. to each part depending on the situation (for example, when the aircraft 1 is in an abnormal state (abnormal)), or it can receive command signals, operation signals, etc. from the outside via the communication unit 91 and transmit command signals, operation signals, etc. to each part. For example, the system has functions such as sending an automatic start signal to the actuator 40 by executing various programs using the CPU when the aircraft 1 is in an abnormal state, and sending a start signal to the actuator 40 by executing various programs using the CPU when a trigger signal is received from a remote signal transceiver operated by an operator.

[0069] Here, examples of the detection unit 90 include a signal receiving sensor, an acceleration sensor, a gyro sensor, a barometric pressure sensor, a GPS (Global Positioning System), a laser sensor, an ultrasonic sensor, an infrared sensor, a millimeter-wave radar, a submillimeter-wave radar, a speed sensor, a monocular or compound-lens vision sensor, an energy sensor, and a wind direction detection sensor, and the detection unit includes at least one of these. Other examples of the detection unit 90 may include detecting when an emergency signal is transmitted from an emergency signal transmitter in response to an operator's operation, or detecting a malfunction of equipment installed on the aircraft 1.

[0070] Furthermore, the above-mentioned "abnormal condition" refers to a situation in which the determination unit 82 determines that the aircraft 1 is in an abnormal state (malfunction, uncontrollable, abnormal fall, etc.) based on signals from the detection unit 90 provided on the aircraft 1 or safety device 100. Specifically, the determination unit 82 determines if: "signal loss from the control unit of the aircraft 1 for a certain period of time or more, or reception of an abnormal signal from the control unit of the aircraft 1"; "signal loss from the remote signal transceiver for a certain period of time or more, or reception of an abnormal signal from the remote signal transceiver"; "if there is communication with a ground station (including a relay station), signal loss from the ground station for a certain period of time or more, or reception of an abnormal signal from the ground station"; "from the position information of the aircraft 1, it is determined that the aircraft 1 is approaching or entering a prohibited area, or has deviated from the planned path"; "the remaining power (battery) or fuel of the aircraft 1 is below a specified value"; "the acceleration of the aircraft 1 is below or above a specified value"; "the angular velocity of the aircraft 1 is above a specified value"; "the attitude angle of the aircraft 1 is above a specified value (for example, horizontal)" This refers to the case where it is determined that one or more of the following conditions have occurred: "The aircraft is tilted at an angle of 45° or more relative to the aircraft," "The aircraft is approaching an obstacle that could cause damage to the aircraft (detected by a laser sensor (such as LiDAR) or infrared sensor, or by a vision sensor and image analysis)," "If the aircraft is capable of carrying a person, an emergency situation has occurred in a person inside the aircraft (detected by an emergency signal being transmitted from an emergency signal transmitter)," "A fatal malfunction of equipment installed on the aircraft is occurring," "The rotation speed of the propulsion unit of the aircraft is below or above a specified value," "An abnormal frequency is detected or a normal frequency is lost regarding the vibration frequency of the aircraft," or "The descent speed of the aircraft is above a specified value."

[0071] The control unit 81 is an example of a starting unit that starts the actuator 40 in at least one of the following cases: when the aircraft 1 is determined to be in an abnormal state, or when the operator of the aircraft 1 gives an instruction to start the actuator 40. As described above, the control unit 81 starts the actuator 40 by sending a signal to the actuator 40 to start the actuator 40. Specifically, the control unit 81 starts the gas generator 49 by sending a signal to the gas generator 49 to start the gas generator 49.

[0072] The control unit 81 is an example of a stopping unit that stops one or more propulsion mechanisms 3 (described later) when the determination unit 82 determines that the aircraft 1 is in an abnormal state. For example, the control unit 81 stops one or more propulsion mechanisms 3 by transmitting a signal to the control unit of the aircraft 1 that controls one or more propulsion mechanisms 3 via the communication unit 91 to stop one or more propulsion mechanisms 3. Specifically, for example, the control unit 81 stops one or more propulsion mechanisms 3 by: "signal interruption or zero throttle signal monopolization between ESC and FC", "signal interruption (PWM or CAN), zero throttle signal monopolization, or power interruption between ESC and aircraft propulsion system (motor or engine)", "signal interruption (PWM or CAN) between FC and aircraft propulsion system (motor or engine)", "transmission of motor stop request to FC", "transmission of motor stop request to companion computer", "transmission of motor signal interruption or current interruption request to PMU", "power interruption between ESC and motor", "power interruption between ESC and PMU", "power interruption between FC and battery", "power interruption between ESC and battery", "power interruption between PMU and battery", "power interruption between PDB and battery", "power interruption between ESC and PDB", "transmission of zero throttle signal from ATS to FC", "transmission of zero throttle signal from ATS to PDB", "transmission of zero throttle signal from ATS to ESC", "motor electromagnetic brake", etc.

[0073] The determination unit 82 determines whether the aircraft 1 is in an abnormal state. As described above, for example, the determination unit 82 determines whether the aircraft 1 is in an abnormal state based on signals received from the detection unit 90, which detects the state of the aircraft 1 (malfunction, uncontrollable, flight state (flight attitude, speed, angular velocity, altitude, attitude angle, etc.), distance to obstacles, position information, etc.). Specifically, for example, the determination unit 82 determines that the aircraft 1 is in an abnormal state if the aircraft 1 is malfunctioning or uncontrollable. The determination unit 82 also determines that the aircraft 1 is in an abnormal state if the flight attitude, speed, angular velocity, altitude, or attitude angle, etc., are above or below a threshold. The determination unit 82 also determines that the aircraft 1 is in an abnormal state if the distance to an obstacle is below a threshold. The determination unit 82 also determines that the aircraft 1 is in an abnormal state if the aircraft 1 is located outside a predetermined range. For example, the determination unit 82 has a CPU, ROM, RAM, etc.

[0074] The memory unit 83 stores the determination data when the determination unit 82 determines that the aircraft 1 is in an abnormal state. For example, the determination data includes the type of abnormality and the time when the abnormality was determined. For example, the memory unit 83 has a ROM, RAM, etc.

[0075] The notification unit 84 notifies the aircraft 1 of the abnormal state by sound and / or light when the determination unit 82 determines that the aircraft 1 is in an abnormal state. For example, the notification unit 84 includes a speaker that emits sounds such as alarms. The notification unit 84 also includes an LED that emits light such as a warning light.

[0076] Next, the aircraft 1 will be described with reference to Figure 8. As shown in Figure 8, the aircraft 1 comprises a body 2, multiple propulsion mechanisms 3, multiple legs 4, and a safety device 100.

[0077] The propulsion mechanism 3 is connected to the airframe 2 and propels the airframe 2. For example, the propulsion mechanism 3 is a propeller or the like. The landing gear 4 is located on the underside of the airframe 2. For example, the safety device 100 is connected to the airframe 2 via the mounting member described above.

[0078] Furthermore, aircraft 2 may have airbags (explosive, hybrid, cylinder, fan, naturally aspirated), floats (hybrid, cylinder, naturally aspirated) positioned separately from the parachute, and warnings (alert, LED). Also, if aircraft 1 is a flying car, aircraft 2 may have impact-absorbing seats for people.

[0079] As described above, the safety device 100 in the first embodiment of the present invention is a safety device for an aircraft 1 and comprises a housing 10 having a bottom 11, a ceiling 12 facing the bottom 11, and a side wall 13 that is divided into a plurality of segments 13a, 13b and supported by the ceiling 12 so that each of the plurality of segments 13a, 13b can rotate outward; a restricting unit 20 that restricts each of the plurality of segments 13a, 13b from rotating relative to the ceiling 12 when the side wall 13 is attached to the bottom 11; an injectable 30 housed in the housing 10; and an actuator 40 that, when activated, removes the side wall 13 from the bottom 11 together with the ceiling 12 and ejects the injectable 30. When the side wall 13 is removed from the bottom 11 by the actuator 40, the restriction by the restricting unit 20 is released, and each of the plurality of segments 13a, 13b becomes rotatable relative to the ceiling 12.

[0080] According to this, when the side wall portion 13 is removed from the bottom portion 11 by the actuator 40, the restriction by the restricting portion 20 is released, and each of the multiple segmented pieces 13a and 13b becomes rotatable relative to the top portion 12. This makes it easier to separate the side wall portion 13 from the injection material 30, and prevents the injection material 30 from getting stuck in the side wall portion 13, thus preventing the injection of the injection material 30 from being obstructed by the side wall portion 13.

[0081] Furthermore, in the safety device 100 according to the first embodiment of the present invention, each of the multiple segmented pieces 13a, 13b is supported on the ceiling portion 12 by a hinge structure so that it can rotate outward.

[0082] According to this, the hinge structure allows each of the multiple segmented pieces 13a and 13b to be easily rotated, thus easily preventing the side wall portion 13 from obstructing the injection of the injection material 30.

[0083] Furthermore, the safety device 100 in the first embodiment of the present invention includes a trigger device 80 having a control unit 81 that activates the actuator 40 in at least one of the following cases: when the aircraft 1 is determined to be in an abnormal state, or when the operator of the aircraft 1 gives an instruction to activate the actuator 40.

[0084] According to this, the actuator 40 can be activated in at least one of the following cases: when the aircraft 1 is determined to be in an abnormal state, or when the operator of the aircraft 1 gives an instruction to activate the actuator 40.

[0085] Furthermore, in the safety device 100 of the first embodiment of the present invention, the aircraft 1 comprises an airframe 2 and one or more propulsion mechanisms 3 coupled to the airframe 2 and propelling the airframe 2, and the trigger device 80 comprises a determination unit 82 that determines whether or not the aircraft 1 is in an abnormal state, and a control unit 81 that stops one or more propulsion mechanisms 3 when the determination unit 82 determines that the aircraft 1 is in an abnormal state.

[0086] According to this, if the aircraft 1 is determined to be in an abnormal state, one or more propulsion mechanisms 3 can be shut down.

[0087] Furthermore, the aircraft 1 in the first embodiment of the present invention comprises an airframe 2, a safety device 100 coupled to the airframe 2, and one or more propulsion mechanisms 3 coupled to the airframe 2 for propelling the airframe 2.

[0088] According to this, it will have the same effects as the safety device 100 described above.

[0089] <Second Embodiment> The safety device according to the second embodiment will now be described with reference to Figure 9. In this embodiment, symbols with the same last two digits as those in the first embodiment are the same and their descriptions may be omitted. Also, parts that are not specifically described are the same as the safety device and aircraft in the first embodiment and their descriptions may be omitted.

[0090] As shown in Figure 9, the safety device 200 according to this embodiment differs from the safety device 100 in that it is equipped with a housing 110 instead of a housing 10.

[0091] The container 110 differs from the container 10 mainly in that it has a ceiling portion 112 instead of a ceiling portion 12, a side wall portion 113 instead of a side wall portion 13, and a support member 114 instead of a support member 14.

[0092] The ceiling portion 112 differs from the ceiling portion 12 mainly in that it has holes 112g and 112h instead of notches 12c and 12d. The holes 112g and 112h penetrate the top plate portion 112a.

[0093] The side wall portion 113 differs from the side wall portion 13 mainly in that it has a hole portion 113e instead of a protruding portion 13c. The hole portion 113e of the divided piece 113a penetrates through the divided piece 113a. The hole portion 113e of the divided piece 113b penetrates through the divided piece 113b.

[0094] Support member 114 differs from support member 14 mainly in that it has string-like members 114c and 114d instead of shafts 14a and 14b. String-like member 114c is passed through hole 112g and hole 113e of segmented piece 113a. This allows segmented piece 113a to rotate outwards, thus supporting it on the top plate portion 112a. String-like member 114d is passed through hole 112h and hole 113e of segmented piece 113b. This allows segmented piece 113b to rotate outwards, thus supporting it on the top plate portion 112a.

[0095] As described above, in the safety device 200 of the second embodiment of the present invention, each of the multiple divided pieces 113a, 113b is supported by the ceiling portion 112 so as to be able to rotate outward by passing string-like members 114c, 114d through holes 112g, 112h provided in the ceiling portion 112 and holes 113e provided in the divided pieces 113a, 113b.

[0096] According to this, the structure through which the string-like members 114c and 114d are passed allows each of the multiple segmented pieces 113a and 113b to be easily rotated, thus easily preventing the side wall portion 113 from obstructing the ejection of the injectable material.

[0097] 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 further includes all modifications within the meaning and scope equivalent to the claims. For example, it is applicable as a safety device for various applications, not limited to aircraft.

[0098] Furthermore, while the above embodiment mentions parachutes or paragliders as the ejected object, it 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 change the inclination angle of the ejected lift-generating member using the control line. This steering mechanism includes, for example, a plurality of reels that wind up a plurality of control lines connected to the lift-generating member, and a motor that powers these reels. By winding up or unwinding the control lines by driving the motor, the lift-generating member can be pulled or released as appropriate.

[0099] 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.

[0100] Furthermore, although the above embodiment described a case in which the side wall portions 13 and 113 are divided into two, the embodiment is not limited to this. For example, the side wall portion may be divided into three or more parts, or may have three or more divided pieces.

[0101] Furthermore, although the above embodiment describes a case in which the segmented pieces 13a, 13b, 113a, and 113b are rotatably supported by the ceiling portions 12 and 112, the invention is not limited to this. For example, contrary to the above embodiment in which the segmented pieces are rotatably provided on the ceiling portion, one end in the sliding direction may be rotatably supported on the bottom, and the other end in the sliding direction may be restricted by a restricting part on the ceiling portion so as not to rotate in its initial state. In this case, when the safety device is activated, the restriction by the restricting part on the ceiling portion side is released, and the segmented piece rotates outward while being supported on the bottom. That is, in this case, when the safety device is activated, the other end of the segmented piece is detached from the ceiling portion, and one end remains connected to the bottom, and is not ejected together with the ceiling portion as in the above embodiment.

[0102] Furthermore, although the above embodiment describes a case in which the divided pieces 13a, 13b, 113a, and 113b rotate in a direction perpendicular to the sliding direction of the piston member 41, the embodiment is not limited to this. For example, as shown in Figure 10, a column portion 212i is provided extending from the outer circumference of the top plate portion 212a toward the bottom side, and the divided pieces 213a and 213b may be supported by the top plate portion 212a via the column portion 212i so that they can rotate around the sliding direction of the piston member. Note that in the initial state, the bottom ends of the divided pieces 213a and 213b are restricted from rotating by a restricting portion similar to the restricting portion provided at the bottom in the first embodiment. The top plate ends of the pair of divided pieces are not restricted from rotating. Furthermore, when the safety device is activated, the bottom ends of the divided pieces 213a and 213b are ejected together with the top plate portion 212a and the column portion 212i, detaching them from the bottom of the container and releasing the restriction, allowing them to rotate as shown in Figure 10.

[0103] Furthermore, in the modified example shown in Figure 10, the bottom ends of the divided pieces 213a and 213b are initially restricted from rotation by a restricting mechanism similar to the one provided at the bottom of the first embodiment, but the invention is not limited to this. For example, a column (similar in shape to the column 212i) may be provided extending from the outer circumference of the bottom of the container toward the top plate, and a pair of divided pieces (similar in shape to the divided pieces 213a and 213b) may be supported at the bottom of the container via the column (similar in shape to the column 212i) so that they can rotate around the sliding direction of the piston member. In this case, the top plate ends of the pair of divided pieces are initially restricted from rotation by a restricting mechanism similar to the one provided at the bottom of the first embodiment. The bottom ends of the pair of divided pieces are not restricted from rotation. Furthermore, when the safety device is activated, the ends of the pair of segmented pieces on the top plate side are detached from the top plate of the container as the ceiling is ejected, and the restriction is released, causing them to rotate in the same direction as segmented pieces 213a and 213b shown in Figure 10. In other words, in this case, when the safety device is activated, the ends of the segmented pieces on the ceiling side are detached from the ceiling and remain connected to the bottom via the column section, and are not ejected together with the ceiling section as in the modified example shown in Figure 10.

[0104] Furthermore, although the above embodiment described a case where the injection unit is an actuator 40, it is not limited to this. For example, the injection unit may be one which uses a gas generator (explosives, cold gas, hybrid, etc.) to push up the injection platform and eject the injector, or one which is a gas-operated piston actuator with a sealing structure (explosives, cold gas, hybrid, etc.), or one which uses gas to inflate an airbag and pushes out the injector with the airbag, or one which uses a compressed spring to push up the injection platform and eject the injector, or one which uses gas from a gas generator (explosives, cold gas, hybrid, etc.) to directly eject the injector.

[0105] Furthermore, although a gas generator was used as the power source in the above embodiment, the configuration is not limited to any device that can provide the sliding member with the driving force necessary to propel the sliding member along the cylinder. For example, an elastic body such as a spring may be used. [Explanation of Symbols]

[0106] 1. Flying object 2 units 3 Propulsion mechanism 4 legs 10,110 containers 11,111 bottom 11a,111a Bottom plate part 11b,111b Wall part 11c,11d,11g,12f,13d,41c,41d,46a,48c,71b,111g,112f,112g,112h,113d,113e Hole 11e, 111e Circular section 11f,13c,111f protrusion 12,112 Ceiling section 12a, 112a, 212a Top plate section 12b, 112b Cylindrical part 12c, 12d Notches 12e Chamfered part 13,113 Side wall section 13a,13b,113a,113b,213a,213b Split piece 14,114 Support members 14a,14b Shaft body 20 Regulatory Department 21,22 pins 30 Projectile 40 Actuators 41 Piston member 41a, 71a Main body 41b Rod-shaped part 41e,46b,46c Groove 42 Tubular member 43 Retaining member 44,47 Sealing member 45,145 cylinders 45a Space 45b Through hole 46 Stopper member 48,148 base 48a Approximately cylindrical member 48b Flange section 48d Insertion port 49 Gas generator 49a Cup body 49b electrode 50 Cylindrical member 60,160 volts 70,170 Harness 71, 73, 173 connectors 72,172 wiring 80 Trigger device 81 Control Unit 82 Judgment section 83 Storage section 84 Hochi Department 90 Detection unit 91 Communications Department 100,200 Safety equipment 114c, 114d String-like member 212i Pillar

Claims

1. A container having a bottom, a ceiling opposite the bottom, and side walls divided into a plurality of segmented pieces, A restricting unit that can restrict each of the plurality of divided pieces from rotating outwards from the container, while each of the plurality of divided pieces is supported by any part of the container other than the divided piece itself, such that each of the plurality of divided pieces can rotate outwards from any part of the container other than the divided piece itself, The injection material contained in the aforementioned container, Upon activation, the injection unit for ejecting the ejected material, along with the ceiling unit, Equipped with, A safety device characterized in that when the ceiling portion is ejected by the injection unit, the restriction by the regulating unit is released, and each of the plurality of segmented pieces becomes rotatable relative to the housing.

2. The restricting portion is provided at the bottom and restricts each of the plurality of segmented pieces from rotating outward relative to the ceiling of the container in the initial state in which the side wall portion is attached to the bottom portion. The safety device according to claim 1, characterized in that the side wall portion is removed from the bottom portion when the injection unit is activated.

3. The restricting portion is provided on the ceiling and restricts each of the plurality of segmented pieces from rotating outward relative to the bottom of the container in the initial state in which the side wall portion is attached to the ceiling portion. The safety device according to claim 1, characterized in that the side wall portion is removed from the ceiling portion when the injection unit is activated.

4. The safety device according to any one of claims 1 to 3, characterized in that each of the plurality of divided pieces is supported on any part of the housing by a hinge structure so as to be rotatable to the outside of the housing.

5. A safety device for aircraft, The safety device according to any one of claims 1 to 3, characterized in that it includes a trigger device having an activation unit for activating the ejection unit in at least one of the following cases: when the aircraft is determined to be in an abnormal state, and when the operator of the aircraft gives an instruction to activate the ejection unit.

6. The aforementioned projectile is a pilot chute, The safety device according to any one of claims 1 to 3, characterized in that it comprises a parachute connected to the pilot chute.

7. 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.

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