Cushioning material for aircraft and aircraft

Abstract

The objective is to obtain a shock-absorbing component for an aircraft that has an impact-absorbing function while being easier to manufacture, and an aircraft equipped with the shock-absorbing component. [Solution] The aircraft 30 comprises a fuselage 31, a safety device 100 coupled to the fuselage 31, one or more propulsion mechanisms (e.g., propellers, etc.) 32 coupled to the fuselage 31 and propelling the fuselage 31, and a plurality of legs 33 provided on the lower part of the fuselage 31. The base 2 connects the housing 18 of the safety device 100 to the fuselage 31 in a position that does not block the hole 24. The legs 33 are cylindrical members (cushion members for aircraft) made of a flexible material and having protrusions 33a and recesses 33b on their side walls. The legs 33 are provided at the four corners of the bottom of the fuselage 31. The side walls of the legs 33 have portions where the tooth traces are twisted in the axial direction to form a helical, substantially oblique tooth shape. The cross-section of the legs 33 cut perpendicular to the axial direction has an uneven shape.

Description

Technical Field

[0001] The present invention relates to a shock absorbing member for an aircraft and an aircraft provided with the shock absorbing member for an aircraft. Background Art

[0002] In recent years, along with the development of autonomous control technology and flight control technology, industrial application of aircraft including a plurality of rotor blades, such as what are called drones, has been accelerating. A drone flies, for example, by rotating a plurality of rotor blades simultaneously in a well-balanced manner; ascending and descending are performed by increasing or decreasing the rotation speed of the rotor blades, and forward and backward movement can be achieved by tilting the airframe through increasing or decreasing the rotation speed of the rotor blades. Such aircraft are expected to expand globally in the future.

[0003] For example, as an example of the aforementioned parachute safety device and an aircraft including the safety device, the application according to Patent Document 1 below can be mentioned. In the aircraft of Patent Document 1, a first buffer plate having a sponge filled layer inside is provided at the bottom of the airframe, buffer springs are provided at four corners of the bottom of the first buffer plate, and a second buffer plate is provided on the buffer springs at the bottom of the first buffer plate. A rubber filled layer is provided inside the second buffer plate. Prior Art Documents Patent Documents

[0004] Patent Document 1 Chinese Patent Application Publication No. 108791824 Specification Summary of the Invention Problems to be Solved by the Invention

[0005] Although the aircraft disclosed in Patent Document 1 can absorb impact at the time of landing or the like, the structure thereof is complicated. Accordingly, there is a demand for a shock absorbing member for an aircraft that can be manufactured more easily while having an impact absorbing function, and an aircraft provided with the shock absorbing member for an aircraft.

[0006] Therefore, the present invention aims to provide a shock-absorbing member for an aircraft that has an impact-absorbing function while being easier to manufacture, and an aircraft equipped with the shock-absorbing member. [Means for solving the problem]

[0007] (1) The cushioning member for an aircraft according to the present invention is characterized in that a cylindrical member made of a flexible material is pre-formed to have the shape of a state when twisted in the direction around the central axis.

[0008] (2) In the cushioning member for the aircraft described in (1) above, it is preferable that the side wall portion of the cylindrical member has a cross-section that is uneven when cut perpendicular to the axial direction, and also has a portion in which the tooth traces are twisted in the axial direction to form a helical, substantially oblique tooth shape.

[0009] (3) The aircraft according to the present invention comprises an airframe, one or more propulsion mechanisms coupled to the airframe and propelling the airframe, and a plurality of legs provided at the bottom of the airframe, wherein the legs are the aircraft cushioning members described in (1) or (2) above, provided so as to substantially coincide the vertical direction of the airframe and the axial direction of the aircraft cushioning members.

[0010] (4) The aircraft described in (3) above is preferably equipped with a safety device that launches and deploys a parachute or paraglider in an emergency. [Effects of the Invention]

[0011] According to the present invention, it is possible to obtain a shock-absorbing member for an aircraft that has an impact-absorbing function while being easier to manufacture, and an aircraft equipped with the shock-absorbing member for an aircraft. [Brief explanation of the drawing]

[0012] [Figure 1] This is a schematic diagram showing an aircraft according to an embodiment of the present invention. [Figure 2]Figure 1 is a schematic diagram showing the legs of the aircraft, where (a) is a perspective view and (b) is a cross-sectional view of the approximate center of (a). [Figure 3] This is a cross-sectional view of the safety device installed on the aircraft shown in Figure 1. [Figure 4] Figure 1 is a block diagram showing the functional configuration of the safety device. [Modes for carrying out the invention]

[0013] Hereinafter, an aircraft according to an embodiment of the present invention will be described with reference to Figures 1 to 3.

[0014] As shown in Figure 1, the aircraft 30 comprises a fuselage 31, a safety device 100 connected to the fuselage 31, one or more propulsion mechanisms (e.g., propellers) 32 connected to the fuselage 31 and propelling the fuselage 31, and a plurality of legs 33 attached to the lower part of the fuselage 31 by adhesive or the like. The base 2 connects the housing 18 of the safety device 100 to the fuselage 31 in a position that does not block the hole 24.

[0015] The leg portion 33 is made of a flexible material (preferably rubber, resin, metal, or other flexible material (including those that can be plastically deformed or have elasticity)) and is a cylindrical member (cushioning member for an aircraft) having a convex portion 33a and a concave portion 33b on its side wall. The cross-sectional shape of the cylindrical member may be any shape, such as a circle, ellipse, polygon, star shape, wave shape, or uneven shape. In this embodiment, the leg portions 33 are provided at the four corners of the bottom of the aircraft body 31 to take balance during landing, but any number of leg portions may be provided as long as they are positioned to stabilize the aircraft body 30 during landing.

[0016] Furthermore, the leg portion 33 is formed by pre-shaping a cylindrical member made of a flexible material in the state when twisted around its central axis. For example, when forming such a leg portion 33 from resin, it can be easily manufactured using a so-called 3D printer. When forming the leg portion 33 from rubber, it may be obtained by cutting it from a block of rubber or by injection molding. When forming the leg portion 33 from metal, it may be obtained by press molding from a plate member.

[0017] In this embodiment, the following leg portion 33 is specifically shown as an example. The side wall portion of the leg portion 33 has a portion in which the tooth trace is twisted in the axial direction (in the direction that substantially coincides with the vertical direction of the machine body 31 when attached to the machine body 31) to form a helical, substantially oblique tooth shape (see Figure 2(a)). In addition, the cross section of the leg portion 33 cut perpendicular to the axial direction has an uneven shape (see Figure 2(b)).

[0018] As described above, since the leg portion 33 is made of the shape and material described above, if a force is applied from at least above or below, for example, it will deform in a twisting direction around the side wall portion. That is, the diameter of the side wall portion of the leg portion 33 will shrink due to the twisting, and the axial length of the leg portion 33 will be shortened. This deformation will allow the applied force to be absorbed. In other words, the leg portion 33 can mitigate the impact when the aircraft 30 lands, and can also prevent rebound during landing.

[0019] Here, as a modification, although the leg portion 33 described above was a cylindrical member, a flat portion may be provided at least one of the upper or lower ends. If a flat portion is provided at the upper end, it is easier to fix it to the bottom surface of the aircraft body 31 by adhesive or the like. Also, if a flat portion is provided at the lower end, the stability of the aircraft body 30 when it lands can be further improved.

[0020] As shown in Figure 3, the safety device 100 comprises an actuator 1, a push-up member 15 pushed up in one direction (upward in Figure 3) by the actuator 1, an ejected object 16 pushed up while being supported by the push-up member 15, a bottomed cylindrical container 18 that accommodates the actuator 1, the push-up member 15 and the ejected object 16, and a lid portion 21 that closes the opening end of the container 18. In the present embodiment, the ejected object 16 is a deployable object such as a parachute or a paraglider. Further, a closing member 60 is provided in the gap between the container 18 and the lid portion 21 to prevent liquid, dust or the like from entering. Any example of the closing member 60 may be used as long as it has waterproof and dustproof functions, and examples thereof include an O-ring, a cured resin, a foam material, and the like. Further, as a modified example of the closing member 60, it may be configured to cover at least the edge of the lid portion 21 and the side portion of the container 18 by wrapping with a film-like member.

[0021] Note that the parachute, which is an example of a deployable body that can be used in the present embodiment, includes those called, for example, "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", and "BALLUTE".

[0022] The actuator 1 includes: a piston member 10 serving as a sliding member; a cylinder 14 that accommodates the piston member 10 and is provided with a hole 13 through which the piston member 10 protrudes outward (upward in FIG. 3) during operation; a base 2 (squib holder) to which one end of the cylinder 14 is caulked and fixed, and which is attached via a hole 25 in the center of the bottom inside the container 18; and a gas generator (such as a micro gas generator) 17 serving as a power source for moving the piston member 10 within the cylinder 14.

[0023] The base 2 includes a substantially cylindrical member 2A that holds, on the cylinder 14 side, the gas generator 17 generating power for sliding the piston member 10, and a flange portion 2B provided on a side of the substantially cylindrical member 2A opposite to the cylinder 14 side.

[0024] The flange portion 2B is machined into a roughly U-shaped, roughly horseshoe shape (not shown), and includes a plurality of holes 2a used for attachment to the housing 18, a plurality of fixing holes (not shown) used for attachment to the airframe 31 of the aircraft 30, and an insertion opening 2c used for inserting a connector 22 for energizing the electrode 17b at the bottom of the gas generator 17. The inner wall of the holes 2a is threaded so that bolts 28, which will be described later, can be screwed into them. The inner wall of the fixing holes (not shown) is also threaded so that bolts (not shown) can be screwed into the aircraft 30 from the airframe 31 side, and the base 2 can be fixed to the airframe 31.

[0025] The connector 22 comprises a main body 22a that can be inserted into the substantially cylindrical member 2A via an insertion opening 2c, a projection (not shown) protruding from the side of the lower part of the main body 22a, and a hole 22c into which the electrode 17b located inside the substantially cylindrical member 2A is fitted. The projection (not shown) is electrically connected to a connector (not shown) that connects to an external power supply via wiring (not shown) extending in a direction perpendicular to the insertion direction of the connector 22 (or radially from the center of the base 2 when mounted on the base 2). The main body 22a also has a hole 22c inside which it is electrically connected to both the electrode 17b and the wiring (not shown) connected to the projection (not shown).

[0026] Furthermore, the insertion opening 2c of the base 2 and the connector 22 are configured such that, when attached to the base 2, they extend radially from the center of the base 2, so that the above-mentioned wiring (not shown) does not block the hole 24.

[0027] The piston member 10 has a main body portion 10a having an outer diameter approximately the same as the inner diameter of the cylinder 14, a rod-shaped portion 10b connected to the main body portion 10a, extending upward and having a smaller diameter than the main body portion 10a, a hole portion 10c provided inside the main body portion 10a and the rod-shaped portion 10b, a female threaded portion 10d provided at the upper end of the rod-shaped portion 10b, and a groove portion 10e provided in the circumferential direction of the main body portion 10a.

[0028] 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.

[0029] As shown in Figure 3, 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.

[0030] 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.

[0031] 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.

[0032] 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.

[0033] A sealing member 11, such as an O-ring, is provided in the circumferential direction in the groove portion 10e.

[0034] 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 3, only two through holes 14a are provided, but multiple through holes may be provided in the circumferential direction.

[0035] 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.

[0036] 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.

[0037] 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.

[0038] 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 3, 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.

[0039] 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.

[0040] 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.

[0041] 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.

[0042] 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.

[0043] As shown in Figure 3, the container 18 comprises a peripheral wall portion 18a and a bottom portion 18b. The bottom portion 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 3, the bottom portion 18b of the container 18 has a recess in the center, and this central portion and the area around it form at least two steps.

[0044] 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.

[0045] 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.

[0046] 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 surface 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 to one end of a bridle line (not shown) attached to the airframe 31 of the aircraft 30 or the containment container 18 via a suspension line (not shown). 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.

[0047] 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.

[0048] 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.

[0049] 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.

[0050] 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.

[0051] 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.

[0052] 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.

[0053] 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.

[0054] 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.

[0055] 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.

[0056] 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.

[0057] 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.

[0058] 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.

[0059] 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.

[0060] 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.

[0061] 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.

[0062] 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).

[0063] In the configuration described above, in an emergency such as when an aircraft 30 equipped with the safety device 100 falls, the calculation unit 222 receives an abnormal signal and the gas generator 17 is activated. From the initial state shown in Figure 3, 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 3). 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.

[0064] According to this embodiment, it is possible to obtain a shock-absorbing member (leg portion 33) for an aircraft that has a shock-absorbing function but is easier to manufacture, and an aircraft 30 equipped with the shock-absorbing member as the leg portion 33. In particular, the leg portion 33 can reduce the impact when the aircraft 30 lands and prevent rebound upon landing. Furthermore, since the leg portion 33 can be easily attached to the aircraft body 31 by adhesive or other means, the complexity of manufacturing the aircraft 30 can be reduced compared to conventional methods.

[0065] 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.

[0066] The safety device only requires 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 does not need to be such that the lid blocks the opening of the container.

[0067] 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.

[0068] 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.

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

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

[0071] Alternatively, the aircraft may be equipped with a safety device capable of launching a net instead of a parachute or paraglider. 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.

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

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

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

[0075] Alternatively, the aircraft may be equipped with a safety device that allows an actuator to eject a so-called paramotor along with its drive mechanism (including a power 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.

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

[0077] Furthermore, the aircraft may be equipped with a safety device that allows an actuator to eject a lighting device (such as a flashlight) along with a drive mechanism (including a power 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.

[0078] Alternatively, the aircraft may be equipped with a safety device that allows an actuator to eject a fire extinguisher along with a drive mechanism (including a 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.

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

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

[0081] Alternatively, the aircraft may be equipped with a safety device that allows an actuator to eject a distress signal transmitter along with a drive mechanism (including a power supply (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.

[0082] Alternatively, the aircraft may be equipped with a safety device that uses an actuator to eject a black box with a parachute (such as a flight recorder) along with a drive mechanism (such as an inflation device including a gas generator), and the drive mechanism to deploy the parachute of the black box when the aircraft crashes. This allows for focused protection of the black box with the parachute. As a result, flight data can be protected. [Explanation of symbols]

[0083] 1 Actuator 2 bases 2A, 3 Cylindrical members 2B Flange section 2a, 10c, 22c, 24, 25, 26, 51, 52, 53 holes 2c insertion slot 3. Cylindrical member 4 Tubular member 5. Retaining member 6 Space 10 Piston member 10a Main body 10b Rod-shaped part 10d Female thread section 10e Groove 11. Sealing member 12 sealing member 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 bottom 19 Bottomed cylindrical part 19a bottom 20 Support part 21 Lid 22 connectors 22a Main body 23 Stopper member 23a, 23b Groove 27 Movement prevention member 28 volts 29 holes 30 flying objects 31 aircraft 33 Legs 33a Convex part 33b Recess 40 Sealing part 50 Bolt Members 50a Head section 50b Male threaded section 53a Insertion opening 60 Closure member 100 safety equipment 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. An aircraft shock absorber characterized by being formed in advance to resemble the shape of a cylindrical member made of a flexible material when twisted around its central axis.

2. The cushioning member for an aircraft according to claim 1, characterized in that the side wall portion of the cylindrical member has an uneven cross-section when cut perpendicular to the axial direction, and has a portion in which the tooth traces are twisted in the axial direction to form a helical, substantially oblique tooth shape.

3. The aircraft and, One or more propulsion mechanisms coupled to the aircraft and propelling the aircraft, Multiple legs provided on the bottom of the aforementioned aircraft, Equipped with, The aircraft is characterized in that the leg portion is the aircraft cushioning member according to claim 1 or 2, provided so that the vertical direction of the aircraft and the axial direction of the aircraft cushioning member substantially coincide.

4. The aircraft according to claim 3, characterized in that it is equipped with a safety device that launches and deploys a parachute or paraglider in an emergency.

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