Safety devices, and aircraft equipped with safety devices

Abstract

We provide safety devices and aircraft equipped with lightning protection. [Solution] The safety device 100 comprises an actuator provided in a housing 18 and supported on a base 2, a push-up member that is pushed up in one direction by the actuator, an injection material that is pushed up while being supported by the push-up member, a bottomed cylindrical housing 18 that houses the actuator, the push-up member, and the injection material, and a lid 21 that closes the open end of the housing 18. The housing 18 is equipped with a discharge unit 70 that discharges the electric charge accumulated in the housing 18.

Description

Technical Field

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

Background Art

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

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

[0004] For example, as an example of the above-mentioned parachute safety device and an aircraft equipped with the safety device, an application according to Patent Document 1 below can be cited. The safety device of this Patent Document 1 opens the lid of a container in which an ejectile is accommodated, and uses a spring in the container whose biasing force is released by an electric motor as a driving force to push out a piston on which the ejectile is placed toward the lid side, and eject the ejectile from the container. The aircraft of Patent Document 1 is equipped with the safety device.

Prior Art Documents

Patent Documents

[0005]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0006] While aircraft equipped with safety devices like those in Patent Document 1 may (1) be damaged by lightning strikes, potentially causing them to crash; (2) be overvoltage caused by lightning strikes, potentially causing the onboard battery to ignite, and the crash of the burning aircraft could lead to a fire on the ground; and (3) be damaged if the aircraft crashes due to a lightning strike, the transported goods and accessories may be damaged. For these reasons, they are not normally flown in weather conditions prone to lightning strikes. However, in recent years, there has been a demand for aircraft equipped with safety devices that can withstand lightning strikes in order to respond to sudden weather changes.

[0007] Therefore, the present invention aims to provide a safety device and an aircraft equipped with lightning protection. [Means for solving the problem]

[0008] (1) The safety device according to the present invention is characterized by comprising: a container for containing an object to be deployed; an ejection unit provided inside the container for ejecting the object to be deployed when activated; and a discharge unit provided outside the container for discharging an electric charge when the container becomes charged.

[0009] (2) In the safety device described in (1) above, it is preferable that the discharge portion is a protruding member that protrudes outward from the housing.

[0010] (3) In the safety device described in (1) or (2) above, it is preferable that the housing is made of a material that can withstand the voltage and current of lightning.

[0011] (4) In the safety device described in (1) or (2) above, it is preferable that the housing is made of a shape or material that discharges lightning current.

[0012] (5) The aircraft according to the present invention comprises an airframe, one or more propulsion mechanisms coupled to the airframe and propelling the airframe, and the safety device according to claim 1 or 2 fixed to the airframe, wherein the discharge section is provided to protrude from the housing toward the opposite side of the direction of travel of the aircraft.

[0013] (6) From another perspective, the flying body according to the present invention may be characterized by comprising: an airframe; one or more propulsion mechanisms coupled to the airframe and propelling the airframe; a discharge unit provided so as to protrude from the airframe toward the opposite direction of travel and for discharging electric charge when the airframe is charged; a housing for housing an object to be deployed; and a safety device provided within the housing for ejecting the object to be deployed when activated. [Effects of the Invention]

[0014] According to the present invention, it is possible to provide a safety device and an aircraft equipped with lightning protection. Specifically, in an aircraft equipped with a lightning protection safety device according to the present invention, or in an aircraft equipped with lightning protection, even if lightning strikes during flight, damage to internal electronic equipment, frame, propellers, etc. can be prevented, the battery can be prevented from catching fire, and the aircraft can be prevented from falling due to a lightning strike. [Brief explanation of the drawing]

[0015] [Figure 1] This is a side view showing the appearance of a safety device (initial state) according to an embodiment of the present invention. [Figure 2] This is a cross-sectional view of the safety device shown in Figure 1, taken along the line AA. [Figure 3] Figure 1 is a schematic diagram showing an aircraft equipped with the safety device. [Figure 4] Figure 1 is a block diagram showing the functional configuration of the safety device. [Figure 5] This is a schematic diagram showing another aircraft equipped with a safety device similar to the one in Figure 1. [Figure 6] This is a schematic diagram showing another aircraft equipped with a safety device similar to the one in Figure 1. [Modes for carrying out the invention]

[0016] Hereinafter, a safety device and an aircraft according to an embodiment of the present invention will be described with reference to Figures 1 to 3.

[0017] As shown in Figures 1 and 2, the safety device 100 comprises an actuator 1, a push-up member 15 pushed up in one direction (upward in Figure 2) 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, and a lid 21 that closes the open end of the container 18. In this embodiment, the injection-molded object 16 is a deployable object such as a parachute or paraglider. A sealing 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 sealing 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 sealing member 60, a film-like material may be used to cover at least the edge of the lid 21 and the side of the container 18.

[0018] Note that a parachute, which is an example of a deployable object that can be used in this embodiment, is, for example, called "FLAT CIRCULAR", "CONICAL", "BICONICAL", "TRICONICAL", "EXTENDED SKIRT", "HEMISPHERICAL", "GUIDE SURFACE", "ANNULAR", "CROSS", "FLAT RIBBON", "CONICAL RIBBON", "RIBBON", "RINGSLOT", "RING SAIL", "DISC-GAP-BAND", "ROTAFOIL", "VORTEX RING", "SANDIA RFD", "PARACOMMANDER", "PARAWING", "PARAFOIL", "SAILWING", "VOLPLANE", "BALLUTE", and the like.

[0019] The actuator 1 includes a piston member 10 which is a sliding member, a cylinder 14 that houses the piston member 10 and is provided with a hole 13 for the piston member 10 to protrude outward (upward in FIG. 2) during operation, a base 2 (squib holder) whose one end of the cylinder 14 is caulked and fixed and is attached through a hole 25 at the center of the bottom inside the container 18, and a gas generator (such as a micro gas generator) 17 as a power source for moving the piston member 10 within the cylinder 14.

[0020] The base 2 includes a substantially cylindrical member 2A that holds the gas generator 17 which generates power for sliding the piston member 10 on the cylinder 14 side, and a flange portion 2B provided on the side opposite to the cylinder 14 side of the substantially cylindrical member 2A.

[0021] 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 projectile 30 described later, and an insertion port 2c used for inserting a connector 22 for energizing the electrode 17b at the lower part of the gas generator 17, and is processed into a substantially U-shaped and substantially horseshoe shape (not shown). Female threads are cut on the inner wall of the hole 2a so that a 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 to the projectile 30 described later so that the base 2 can be fixed to the airframe 31.

[0022] 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 part 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 through 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).

[0023] 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 hole portion 24.

[0024] 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 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 thread portion 10d provided at the upper end portion of the rod-shaped portion 10b, and a groove portion 10e provided in the circumferential direction of the main body portion 10a.

[0025] At least the upper end of the rod-shaped portion 10b has a non-circular cross-section, although this is not shown in the figure. Here, a non-circular shape includes, for example, a polygonal shape, an elliptical shape, a star shape, or a gear shape, but any shape that is non-circular is included. Furthermore, at the lower part of the rod-shaped portion 10b, the tubular member 4 is fitted or loosely fitted with the main body portion 10a with one end in contact. There may be a gap between the inner wall of the tubular member 4 and the outer wall of the rod-shaped portion 10b, but this gap should be within a range that does not hinder the plastic deformation due to substantially uniform compression during impact, which will be described later.

[0026] As shown in Figure 2, the tubular member 4 is held by the holding member 5 at the lower part of the rod-shaped portion 10b, with one end in contact with the main body portion 10a. The tubular member 4 is made of a material that is plastically deformable and has a tensile strength lower than that of the piston member 10 and the stopper member 23 described later (for example, metals such as iron, aluminum, brass, copper, alloys such as stainless steel, resins, etc.). Here, the holding member 5 may be an elastic material such as rubber, or it may be made of the same material as the tubular member 4, and its shape may be ring-shaped or clip-shaped.

[0027] Furthermore, to prevent the tubular member 4 from contacting the inner wall of the cylinder 14, the tubular member 4 and the inner wall of the cylinder 14 are separated by a predetermined distance or more (for example, a distance at which the tubular member 4, which has undergone plastic deformation due to substantially uniform compression upon impact with the stopper member 23, will not come into contact with the inner wall of the cylinder 14). As a result, even if the tubular member 4 undergoes plastic deformation upon impact with the stopper member 23, it will deform without being hindered by the inner wall of the cylinder 14, and the impact on the piston member 10 will be sufficiently mitigated.

[0028] 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.

[0029] 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.

[0030] A sealing member 11, such as an O-ring, is provided in the circumferential direction in the groove portion 10e.

[0031] 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 2, only two through holes 14a are provided, but multiple through holes may be provided in the circumferential direction.

[0032] 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.

[0033] 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 through the gap between the outer wall of the cylinder 14 and the inner wall of the bottomed cylindrical part 19, passing through the inside of the container 18, and the gas pressure causes the sealing part 40 (sealing material) described later to break, and the gas is released to the outside of the container 18 from the hole 24, thus preventing the cylinder 14 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 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.

[0034] 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.

[0035] 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 2, 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 opening 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.

[0036] The bottomed cylindrical portion 19 has a bottom portion 19a that is roughly flat or roughly columnar (roughly columnar in this embodiment), a hole portion 51 formed on the lid portion 21 side of the bottom portion 19a, a hole portion 52 (second hole portion) with a smaller diameter than the hole portion 51, and a hole portion 53 (first hole portion) that communicates with the hole portion 51 via the hole portion 52 and has a larger diameter than the hole portion 52. The hole portion 51 has a diameter larger than the diameter of the head portion 50a of the bolt member 50. The hole portion 52 has a diameter smaller than the diameter of the head portion 50a and can guide the male threaded portion 50b of the bolt member 50 inserted from the hole portion 51 side to the hole portion 53 side. The hole 53 is substantially the same shape as one end (upper end) of the rod-shaped portion 10b, and when one end of the rod-shaped portion 10b is inserted through the insertion opening 53a provided on the cylinder 14 side of the bottom 19a of the bottomed cylindrical portion 19, it becomes a fitting portion into which one end of the rod-shaped portion 10b fits.

[0037] 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.

[0038] The support portion 20 is initially positioned spaced apart from the inner surface of the bottom of the container 18. The support portion 20 also has a hole portion 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 come into contact with the inside of the container 18. At least one (eight in this embodiment) movement prevention member 27 is provided on the upper surface of the support portion 20 to prevent the bottomed cylindrical portion 19 of the injectable 16 from moving in the circumferential direction.

[0039] 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.

[0040] As shown in Figures 1 and 2, the housing 18 comprises a peripheral wall portion 18a and a bottom portion 18b. As shown in Figure 1, the peripheral wall portion 18a is a protruding member that extends from the outer wall portion and includes a discharge portion 70 that discharges the charge accumulated in the housing 18 due to current from lightning or static electricity. The discharge portion 70 is, for example, called a discharge cable or static discharger, and is a rod-shaped, rope-shaped with a frayed end, or wire-shaped component attached one or more (preferably multiple), and is made of a conductive material (for example, a bundle of metal or conductive fibers). The cause of static electricity is that when an aircraft 30 equipped with the safety device 100 shown in Figure 3 flies at high speed within the atmosphere, friction occurs between the air and the surface of the aircraft 31 and the safety device 100, causing static electricity to accumulate on the safety device 100 and the aircraft 31. The discharge portion 70 is the part that continuously discharges these static electricity charges into the air. Even if lightning strikes the flying object 30, the charge can be released (discharged) from the discharge section 70. Preferably, the housing 18 is made of a material that can withstand the voltage and current of lightning (for example, polycarbonate (PC), carbon fiber reinforced plastic (CFRP), etc.). Furthermore, preferably, the housing 18 is made of a shape (for example, with sharp edges) or material (for example, copper, aluminum tape, etc.) that allows for the discharge of lightning current.

[0041] As shown in Figure 2, the bottom 18b of the container 18 is provided with a plurality of holes 24 that connect the inside and outside of the container 18, a hole 25 into which the base 2 is inserted, and holes 29 for bolt fastening. Also, as shown in Figure 2, the bottom 18b of the container 18 has a recess in the center, and this central part and the area around it form at least two steps.

[0042] A sealing portion 40 (sealing material) is attached to the container 18 side of each of the multiple holes 24. This sealing material is designed to break due to the negative pressure generated between the support portion 20 and the bottom of the container 18 during operation, and is, for example, a tape-like material. When the push-up member 15 moves rapidly inside the container 18, negative pressure is generated in the area between the push-up member 15 and the bottom surface of the container 18. This makes it difficult to move the push-up member 15. By providing the holes 24, the negative pressure phenomenon can be reduced, and the push-up member 15 can be moved smoothly. However, before operation, the sealing portion 40 (sealing material) is provided to prevent the intrusion of liquids, dust, etc. into the container 18 and to prevent deterioration and damage to the injection material 16.

[0043] 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, to the inside of the container 18 with a bolt 28 through a hole 29. 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.

[0044] The injection 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 injection material 16 is folded so that its outer side is in contact with the inner wall surface of the peripheral wall portion 18a of the containment container 18. The injection material 16 is connected via a suspension line (not shown) to one end of a bridle line (not shown) attached to the airframe 31 of the aircraft 30 or the containment container 18, as described later. As one modification, the injection material 16 may be folded in a bellows-like manner (with a wave-shaped cross-section) from its edge toward the center, or it may be folded in any other way.

[0045] Here, the injection-molded product 16 in this embodiment is, for example, a parachute or paraglider. The base fabric of the parachute or paraglider is preferably formed by weaving together at least one fiber from among polyamide, polyester, polyimide, vinyl chloride, polycarbonate, acrylic, and polyolefin fibers. For example, it may be a base fabric made by joining together multiple fabrics formed by weaving together one type of fiber, or a base fabric made by joining together a fabric made by weaving together one type of fiber and a fabric made by weaving together other fibers, or a base fabric made by weaving together multiple types of fibers. Furthermore, the base fabric of the parachute or paraglider may consist of at least one film made from polyamide, polyester, polyimide, vinyl chloride, polycarbonate, acrylic, or polyolefin resins. For example, it may be a base fabric made by joining together multiple films of one type, or a base fabric made by joining together multiple types of films. The joining of the above-mentioned fabrics or films may be carried out by any means, such as pressure bonding, adhesive bonding, or sewing.

[0046] Examples of polyamide fibers or resins include nylon 6, nylon 6,6, and nylon 4,6. Examples of polyester fibers or resins include polyethylene terephthalate, polybutylene terephthalate, polyethylene naphthalate, and polybutylene succinate. Examples of polyimide fibers or resins include aromatic polyimide and aliphatic polyimide. Examples of vinyl chloride fibers or resins include vinyl chloride film, examples of polycarbonate fibers or resins include polycarbonate film, examples of acrylic fibers or resins include acrylic film, and examples of polyolefin fibers or resins include low-density polyethylene, high-density polyethylene, and polypropylene. The base fabric may be coated with a coating agent such as silicone or polyurethane.

[0047] 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.

[0048] 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.

[0049] Furthermore, as shown in the schematic diagram of the aircraft 30 in Figure 3, the safety device 100 is connected and fixed to the aircraft body 31 of the aircraft 30 by bolts (not shown) from the aircraft body 31 side via fixing holes (not shown) of the base 2, so that the discharge section 70 protrudes in the opposite direction to the direction of travel (direction of the arrow in Figure 3). By positioning the discharge section 70 to protrude in the opposite direction to the direction of travel (direction of the arrow in Figure 3), it is made easier for the charge to escape from the discharge section 70 (to discharge). It is also preferable that the discharge section 70 is installed on the upper part of the safety device 100, and it is even more preferable that it protrudes at an angle upward. When the safety device 100 is installed on the upper part of the aircraft 30 as shown in Figure 3, the discharge section 70 is located at the very top of the aircraft 30, so discharge can be performed efficiently. In addition, electromagnetic waves generated during discharge are less likely to affect equipment, so malfunctions of electronic equipment can be prevented. At this time, as shown in Figure 3, the base 2 connects the housing 18 and the aircraft body 31 in a position that does not block the hole 24. Therefore, the aircraft body 30 comprises the 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 and propelling the aircraft body 31, and a plurality of legs 33 provided on the lower part of the aircraft body 31.

[0050] 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.

[0051] Furthermore, the safety device 100 includes an abnormality detection device 200 (not shown in Figure 3) which includes an acceleration sensor and the like for detecting abnormalities in the aircraft 30.

[0052] Here, the functional configuration of the anomaly detection device 200 will be described. As shown in Figure 4, the anomaly detection device 200 comprises a sensor (detection unit) 210 and a control unit (computer having a CPU, ROM, RAM, etc.) 220, and is electrically connected to the igniter in the gas generator 17 of the injection unit, the memory unit 201, the flight control unit 202, and the notification unit 203.

[0053] Sensor 210 detects the flight status of the aircraft 30 (including collisions, crashes, etc.). Specifically, sensor 210 is a sensor selected from one or more of the following: an accelerometer, gyroscope, barometric pressure sensor, laser sensor, infrared sensor, monocular / compound vision sensor, ultrasonic sensor, voltmeter, fuel gauge, etc. It can acquire data on the flight status of the aircraft 30, such as its speed, acceleration, angular acceleration, tilt, altitude, position, and obstacles that may hinder the flight of the aircraft 30, as well as data on the surrounding environment (obstacles, terrain, building shapes, etc.), power supply, fuel level, etc.

[0054] The control unit 220 functionally comprises an anomaly detection unit 221, a calculation unit 222, and a notification unit 223. These anomaly detection unit 221, calculation unit 222, and notification unit 223 are functionally realized when the control unit 220 executes a predetermined program.

[0055] The anomaly detection unit 221 not only detects abnormal conditions related to the surrounding environment based on information received from the sensor 210, but also detects the flight status of the aircraft 30 (whether it is in an abnormal state such as falling during flight). In other words, the anomaly detection unit 221 detects whether the sensor 210 and the aircraft 30 are able to operate normally. For example, the anomaly detection unit 221 can detect the emergency status of personnel inside the aircraft 30, a fatal failure of equipment inside the aircraft 30, the power supply (battery) of the aircraft 30 being below a preset value, the fuel amount of the aircraft 30 being below a preset value, the acceleration or angular velocity of the aircraft 30 being above or below a preset value, the attitude angle of the aircraft 30 being above a preset value, the descent speed of the aircraft 30 being above a preset value, etc. Furthermore, if the aircraft 30 is being operated by an operator using a controller, the anomaly detection unit 221 can detect the loss of operation signals from the controller or the reception of an abnormal signal. Furthermore, the anomaly detection unit 221 can detect the loss of a signal from a ground station or the reception of an abnormal signal.

[0056] The calculation unit 222 determines whether the flight state of the aircraft 30 is abnormal based on the data acquired by the sensor 210. Specifically, the calculation unit 222 determines abnormalities by comparing the data acquired by the sensor 210 with preset threshold values. The calculation unit 222 also receives obstacle detection signals, distance detection signals, altitude detection signals, etc., from the sensor 210 in real time and determines abnormalities based on these received signals. Furthermore, the calculation unit 222 determines whether the aircraft 30 is approaching or entering a prohibited area, or deviating from the planned route, based on the aircraft 30's position information.

[0057] Furthermore, if the calculation unit 222 determines that the flight status of the aircraft 30 is abnormal, it outputs an abnormality signal (which may include command signals to activate or operate other equipment) to the outside. Alternatively, an abnormality signal output unit may be provided separately from the calculation unit 222, and this abnormality signal output unit may be configured to output an abnormality signal in response to a command from the calculation unit 222.

[0058] The notification unit 223 notifies the administrator or other relevant party that an anomaly has been detected when the anomaly detection unit 221 detects an anomaly in the sensor 210 or the aircraft 30.

[0059] The memory unit 201 is capable of storing various types of data, such as data acquired by the sensor 210 and judgment data when an abnormality is detected by the calculation unit 222.

[0060] The flight control unit 202 controls the flight attitude of the aircraft 30, and if an abnormality is detected by the calculation unit 222, it can stop the propulsion system (motor, etc.) installed on the aircraft 30.

[0061] The notification unit 203 is capable of notifying the surroundings of an abnormality when the calculation unit 222 determines that an abnormality has occurred. For example, the notification unit 203 can notify the surroundings of the abnormality by activating a sound generating device (such as an alarm) and / or a lighting device (such as an LED).

[0062] In the configuration described above, when an aircraft 30 equipped with the safety device 100 falls, the calculation unit 222 receives an abnormal signal and the gas generator 17 activates. From the initial state shown in Figure 2, the pressure of the gas generated by this activation pushes the piston member 10 upward within the cylinder 14. As a result, the push-up member 15, which has a bottomed cylindrical portion 19 connected to the rod-shaped portion 10b of the piston member 10, is pushed 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 from inside the container 18 outward (upward in the plane of the paper in Figure 2). In addition, negative pressure is generated in the area between the support portion 20 of the push-up member 15 and the bottom surface of the container 18, causing the sealing portion 40 (sealing material) to rupture and outside air to flow into the container 18 from outside the hole 24. Next, the piston member 10 and the tubular member 4 move upward, but the tubular member 4 collides with the stopper member 23 and stops. Then, if the projectile 16 is a parachute or paraglider, the projectile 16 is ejected from the container 18 and then deployed.

[0063] According to this embodiment, it is possible to provide an aircraft 30 equipped with a safety device 100 that is protected against lightning strikes. Furthermore, even if lightning strikes the aircraft 30 during flight, damage to the internal electronic equipment, frame, propellers, etc. can be prevented, the power supply (battery) can be prevented from catching fire, and the aircraft can be prevented from falling due to a lightning strike.

[0064] 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.

[0065] For example, as shown in Figure 5, a safety device 101 similar to the safety device 100 may be attached to a base 134 provided on the side wall of the machine body 131. In this case as well, the discharge section 170 is provided to protrude toward the opposite side of the direction of travel (the direction of the arrow in Figure 5). This allows for efficient discharge and reduces the impact of electromagnetic waves generated during discharge on equipment, thereby preventing malfunctions of electronic equipment. Note that parts similar to those in the above embodiment are denoted by the same last two digits as the above embodiment, and their description is omitted. Also, in this embodiment, parts that are not specifically described are the same as in the above embodiment, and their description is omitted. The same applies to the following description.

[0066] Furthermore, as shown in Figure 6, the safety device 102, which does not have a discharge section, may be located on the upper part of the machine body 231, and the discharge section 270 may be located on the side wall of the machine body 231. In this case as well, the discharge section 170 is provided so as to protrude toward the opposite side of the direction of travel (the direction of the arrow in Figure 6). This allows for efficient discharge and reduces the likelihood of electromagnetic waves generated during discharge affecting equipment, thereby preventing malfunctions of electronic equipment. The safety device 102 may also be provided with a discharge section similar to the discharge section 70 in the above embodiment.

[0067] Furthermore, the safety device only needs to have an injection section inside the container for ejecting the material, and the shape of the container can be anything, such as a fan-shaped or rectangular cross-section, and it is also fine if the lid does not block the opening of the container.

[0068] Furthermore, in the above embodiment, a portion of the base was configured to be located outside the container, but the entire base may be configured to be located inside the container.

[0069] Furthermore, although a gas generator was used as the power source in each of the above embodiments, the configuration is not limited as long as it is possible to provide the sliding member with the driving force necessary for the sliding member to propel itself within the cylinder. For example, an elastic type using an elastic body such as a spring, a gas cylinder type using gas pressure confined in a container, or a chemical reaction type (non-explosive) that generates gas pressure by mixing two or more substances and causing a chemical reaction may be used as the power source. In addition, a pull-out type (also called a tension type) ejection device may be used instead of the ejection device of the above embodiments and modified examples. Examples of such pull-out type ejection devices include a method in which a rocket is launched and a parachute is pulled out, a method in which a weight is launched with an actuator and then a parachute is pulled out, a method in which a projectile is launched with an actuator and then a parachute is pulled out, and a method in which a pilot chute, which is initially housed in another container, is launched by the ejection device, and the parachute is pulled out from the container according to the present invention by the pilot chute.

[0070] Furthermore, in each of the above embodiments, if a parachute or paraglider is used as the projectile, the parachute or paraglider may be packed. The packing is configured to tear or peel off during operation.

[0071] Furthermore, while the above embodiments mention parachutes or paragliders as the ejected objects, the invention is not limited to these, and objects including lift-generating members may also be ejected. Examples of lift-generating members include parafoils, Rogallo-type parachutes, single-surface parachutes, airplane wings, propellers, balloons, etc. If the lift-generating member has a control line, it is desirable that the safety device includes a steering mechanism that can use the control line to change the inclination angle of the ejected lift-generating member. This steering mechanism may include, for example, a plurality of reels that wind up a plurality of control lines connected to the lift-generating member, and a motor that powers these reels. By winding up or unwinding the control lines by driving the motor, the lift-generating member can be pulled or released as appropriate.

[0072] 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.

[0073] 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.

[0074] 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.

[0075] 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.

[0076] 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 source (battery) 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.

[0077] 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 (battery) 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.

[0078] 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 source (battery) 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.

[0079] 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 drive unit such as a power source (battery)), and the drive mechanism to activate the fire extinguisher when the aircraft crashes, thereby spraying fire extinguishing agent onto the aircraft and its surroundings.

[0080] 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.

[0081] 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.

[0082] 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 (battery) 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.

[0083] 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]

[0084] 1 Actuator 2 bases 2A, 3 Cylindrical members 2B Flange section 2a, 10c, 22c, 24, 25, 26, 51, 52, 53 holes 2c insertion slot 4 Tubular member 5. Retaining member 6 Space 10 Piston member 10a, 22a Main body 10b Rod-shaped part 10d Female thread section 10e, 23a, 23b groove 11, 12 Sealing members 13 Hole 14 cylinders 14a Through hole 15 Push-up member 16 Projectile 17 Gas generator 17a Cup Body 17b Electrode 18 containers 18a Peripheral wall part 18b, 19a bottom 19 Bottomed cylindrical part 20 Support part 21 Lid 22 connectors 23 Stopper member 27 Movement prevention member 28 volts 29 holes 30, 130, 230 flying objects 31, 131, 231 aircraft 32, 132, 232 Propulsion mechanism 33, 133, 233 Legs 40 Sealing part 50 Bolt Members 50a Head section 50b Male threaded section 53a Insertion opening 60 Closure member 70, 170, 270 discharge section 100, 101, 102 Safety devices 134 Pedestal 200 Anomaly detection device 201 Storage section 202 Flight Control Unit 203 Hochi Department 210 sensors 220 Control Unit 221 Anomaly detection unit 222 Arithmetic section 223 Notification Department

Claims

1. A containment device for housing the deployed object, An injection unit is provided within the container and ejects the object to be deployed when it is activated, A discharge unit is provided on the outside of the container and discharges the charge when the container becomes charged, A safety device equipped with [unspecified features].

2. The safety device according to claim 1, characterized in that the discharge portion is a protruding member provided so as to protrude outward from the housing.

3. The safety device according to claim 1 or 2, characterized in that the housing is made of a material that can withstand the voltage and current of lightning.

4. The safety device according to claim 1 or 2, characterized in that the housing is made of a shape or material that discharges lightning current.

5. The aircraft and, One or more propulsion mechanisms coupled to the aircraft and propelling the aircraft, The safety device according to claim 1 or 2, fixed to the aircraft body, An aircraft equipped with, The discharge section is provided so as to protrude from the housing toward the opposite side of the direction of travel of the flying body.

6. The aircraft and, One or more propulsion mechanisms coupled to the aircraft and propelling the aircraft, A discharge unit is provided so as to protrude from the aircraft body toward the opposite side of the direction of travel, and discharges the charge when the aircraft body becomes charged, A safety device comprising a container for housing an object to be deployed, and an ejection unit provided within the container for ejecting the object to be deployed when activated, An aircraft characterized by having the following features.

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