JP2018001814A - Parachute and aircraft with parachute system - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a parachute system that can prevent dew condensation from occurring in a parachute and cause the parachute to be opened more surely when an unexpected accident occurs in an aircraft to make the aircraft land relatively safely.SOLUTION: The present invention relates to a parachute system comprising a pilot chute, a main parachute and a heater, in which the pilot chute is connected to the canopy of the main parachute, and the heater is installed in a manner capable of preventing dew condensation from occurring in the pilot chute and the main parachute.SELECTED DRAWING: Figure 1

Description

  The present invention relates to a parachute system and an aircraft including the parachute system.

  With the development of technology in recent years, drones that can fly unattended are being developed. Because drones cannot be controlled by the pilot, drones are more likely to crash in the event of a sudden accident, such as a breakdown, gust, or lightning strike.

  If a drone crashes, the damage caused by the precision machine installed in the drone and the data collected by the drone, or by crashing into a person or building on the ground, will be extremely severe. For this reason, when manufacturing or using a drone, it is necessary to assume a risk of the drone falling and to devise a drone to reduce the risk of the drone as much as possible.

  By the way, conventionally, a parachute has been widely used for the purpose of lowering a person or the like from an aircraft or the like or decelerating the aircraft or the like. For example, Patent Document 1 describes a parachute that decelerates an aircraft in two stages by including a first stage parachute that opens at the first stage and a second stage parachute that opens at the second stage.

JP 2010-18264 A

  However, in order to reduce the falling speed when the drone crashes, using a parachute as described in Patent Document 1 is useful for a drone flying at a low altitude, but it is allowed to fly at a high altitude. Drones are not always useful and have various problems.

  For example, at high altitudes, the temperature and pressure are low, so condensation tends to occur on the parachute. When condensation occurs on the parachute, the parachute is difficult to open due to the surface tension or freezing of the condensed water, which causes a problem that the drone falling speed cannot be reduced.

  The present invention has been made in view of the above problems. In other words, the present invention can prevent dew condensation on the parachute and can open the parachute more reliably and land the aircraft relatively safely when a sudden accident occurs in the aircraft. Is to provide a simple parachute system.

  The present invention relates to the following aspects [1] to [8].

[1] A pilot chute, a main parachute, and a heater are provided.
The pilot shoot is connected to the main parachute canopy,
A parachute system in which a heater is installed in a manner capable of preventing condensation on the pilot chute and the main parachute.

[2] An exterior that can accommodate the pilot chute and the main parachute is provided.
The parachute system according to [1], wherein the exterior is made of an aluminum heat insulating sheet.

[3] State detection means capable of detecting the state of the aircraft in which the parachute system is installed;
State determination means capable of determining whether or not the detected state satisfies a predetermined condition;
The parachute system according to [1] or [2], further comprising: a discharge control unit that performs control so that the pilot chute can be discharged when the state satisfies a predetermined condition.

  [4] The parachute system according to [3], wherein the state detection unit includes at least one sensor selected from the group consisting of an altitude sensor, a three-axis tilt sensor, a temperature sensor, a drop speed sensor, and a battery sensor.

[5] Provided with a receiving means capable of receiving specific information from the aircraft in which the parachute system is installed,
The parachute system according to [3] or [4], wherein the state detection unit is capable of detecting reception of specific information as a state indicating that the aircraft is operating normally.

[6] An air hole and a fan capable of blowing air into the air hole,
The discharge control means performs control to operate the fan when a predetermined condition is satisfied,
The parachute system according to any one of [3] to [5], wherein the pilot chute can be swollen and discharged by the air that has passed through the air hole.

  [7] The parachute system according to any one of [1] to [6], further including a power supply connector that receives power supply from an electric power source of an aircraft in which the parachute system is installed.

  [8] An aircraft including the parachute system according to any one of [1] to [7].

  According to the parachute system of the present invention, it is possible to prevent dew condensation on the parachute and to open the parachute more reliably when a sudden accident occurs in the aircraft. As a result, even when a sudden accident occurs in the aircraft, the aircraft can be landed relatively safely.

It is a typical schematic diagram showing the parachute system concerning an embodiment of the invention. It is a typical schematic diagram showing the opening style of a parachute system concerning an embodiment of the invention.

  In this specification, “aircraft” is a general term for various flying objects such as drones, model aircraft, rotary wing aircraft, gliders, airships, and airplanes. In addition, the term “aircraft” in the present specification is a term encompassing both those capable of unmanned flight and those capable of manned flight.

  "Drone" is a term that generally refers to something that can be unmanned flight, so that a drone that is capable of unmanned flight, such as a rotorcraft, may be interpreted as being included in a drone . Examples of rotary wing aircraft include multicopters such as tricopters, quadcopters, hexacopters, or octocopters.

  The parachute system of the present invention can be installed in an aircraft regardless of the type of the aircraft, regardless of whether the aircraft is manned or unmanned.

  Hereinafter, although the parachute system which concerns on embodiment of this invention is demonstrated using drawing, this invention is not limited to drawing and embodiment. For convenience, an embodiment in which a parachute system is installed in a drone will be described. However, an aircraft in which a parachute system according to an embodiment of the present invention can be installed is not limited to a drone.

  FIG. 1 is a schematic diagram showing a parachute system according to an embodiment of the present invention. A parachute system 10 shown in FIG. 1 includes an exterior 11, a pilot chute 12, a main parachute 13, an air hole 14, a discharge control means 15, and a power supply connector 16. In addition, components not shown such as a heater are appropriately mounted.

  The exterior 11 can accommodate the pilot chute 12, the main parachute 13, the air holes 14, and the discharge control means 15. The shape of the exterior 11 will not be specifically limited if it is a shape which can accommodate said component.

  Although the material of the exterior 11 is not specifically limited, For example, a metal, a plastic, a cloth material etc. can be used. Among them, the aluminum heat insulating sheet is particularly preferable from the viewpoint of keeping the inside of the exterior 11 heated by the heater and preventing dew condensation because it is excellent in heat resistance, cold resistance, incombustibility, and the like. In addition, in order to make it hard to produce dew condensation, it is good also as an aspect which provides a desiccant etc. in the inside of the exterior 11 suitably.

  In addition, an upper lid or the like is provided on the upper side of the outer casing 11, that is, on the side where the pilot chute 12 and the main parachute 13 are discharged, so that the pilot chute 12 and the main parachute 13 are not discharged normally. Good. In this case, it is preferable that the discharge control means 15 performs control to open the upper lid when the pilot chute 12 is discharged.

  The pilot chute 12 is connected to the canopy of the main parachute 13. With the above configuration, when the pilot chute 12 is discharged, the main parachute 13 is pulled out by the pilot chute 12, so that the main parachute 13 is more reliably discharged. The pilot chute 12 is housed inside the exterior 11 and folded over the main parachute 13.

  The pilot chute 12 is preferably accommodated so that the back surface of the canopy of the pilot chute 12 is positioned in the vicinity of the exhaust port of the air hole 14. With the above-described configuration, the pilot chute 12 can easily swell and can be opened easily.

  The main parachute 13 is housed inside the exterior 11 and folded under the pilot chute 12. Examples of the connection location of the main parachute 13 include the air holes 14 and the exterior 11, but are not particularly limited.

  The pilot chute 12 is preferably opened quickly, and the main parachute 13 is preferably capable of suitably reducing the drone falling speed. Therefore, the area of the canopy of the pilot chute 12 is smaller than the area of the canopy of the main parachute 13. It is preferable.

  The material of the pilot chute 12 and the main parachute 13 is not particularly limited, but it is preferable to use ripstop nylon or the like from the viewpoint of preventing condensation or tearing.

  In the parachute system 10 according to the present embodiment, the state as shown in FIG. 2A (the state shown in FIG. 1) is a normal state. When a predetermined condition is satisfied, the pilot chute 12 accommodated in the exterior 11 is discharged to the outside of the exterior 11 and opened as shown in FIG. Since the pilot chute 12 is connected to the canopy of the main parachute 13, as shown in FIG. 2 (c), the main parachute 13 is also discharged to the outside of the exterior 11 as the pilot chute 12 is discharged. As shown in d), the main parachute 13 can be opened.

  As a discharge control means for controlling the pilot chute and the main parachute to be discharged, it is possible to adopt a mode in which the pilot chute and the main parachute are discharged by adopting an extruding means such as a piston. From the viewpoint of facilitating the opening, the discharge control means 15 performs control to operate a fan (not shown) when a predetermined condition is satisfied, and air is blown into the air hole 14 by the fan, The pilot chute 12 is preferably inflated and discharged by the air that has passed through the air holes 15. By inflating and discharging the pilot chute 12, the pilot chute 12 can be quickly opened. As a result of the quick opening of the pilot chute 12, the main parachute 13 is also quickly discharged.

  The exhaust port of the air hole 14 is opened near the back surface of the canopy of the pilot chute 12 as described above. In FIG. 1, the intake port of the air hole 14 is provided on the lower side of the exterior 11, that is, on the side opposite to the side from which the pilot chute 12 and the main parachute 13 are discharged. The opening position is not particularly limited.

  The shape of the air hole 14 is not particularly limited as long as it is a shape capable of blowing air, but from the viewpoint of preventing the pilot chute 12 and the main parachute 13 from being broken when the pilot chute 12 and the main parachute 13 are discharged, It is preferable to do.

  In addition, it is good also as a structure which provides a lower cover etc. in the inlet of the air hole 14, and does not take in air normally. In this case, it is preferable that the discharge control means 15 performs control to open the lower lid when the pilot chute 12 is discharged.

  The fan installation position is not particularly limited as long as it is a position where air can be blown into the air hole 14. For example, the fan can be installed inside the air hole 14 or in the vicinity of the air inlet of the air hole 14.

  The parachute system 10 is preferably configured to receive power supply from a power source such as a battery mounted in advance on the drone via the power supply connector 16. With the above configuration, it is possible to eliminate the necessity of mounting a battery or the like on the parachute system 10 itself.

  When the power supply connector 16 is provided in the discharge control means 15, it is preferable to provide a wiring hole in the exterior 11. Moreover, in order to ensure the airtightness inside the exterior 11 and to prevent dew condensation, it is preferable to provide the power supply connector 16 in the exterior 11. When the power supply connector 16 is provided on the exterior 11, the exterior 11 and the discharge control means 15 are integrally formed at the place where the power supply connector 16 is provided, or the power supply connector 16 is connected to the discharge control means 15. It is preferable to provide a cable to be used.

  The parachute system 10 according to the present embodiment includes a heater (not shown). The type and installation location of the heater are not particularly limited as long as it is an aspect that can prevent condensation on the pilot chute 12 and the main parachute 13.

  The type of the heater is not particularly limited. For example, it is preferable to use a device that generates heat or a device that convects hot air. By using the apparatus as described above, it is possible to prevent condensation from occurring with high energy efficiency.

  Although the installation location of the heater is not particularly limited, for example, it is preferable to install the heater on the inner surface of the exterior 11 or the outer surface of the air hole 14. By installing in the said location, it can prevent that dew condensation arises, without preventing discharge | emission of the pilot chute 12 and the main parachute 13. FIG.

  Since the pilot chute 12 is also a key for opening the main parachute 13, a larger number of heaters are installed on the pilot chute 12 than the main parachute 13, the heater installation density is increased, It is preferable that the temperature of the heater is increased so that condensation does not occur more in the pilot chute 12 than in the main parachute 13.

  Moreover, it is preferable that a heater is installed so that the upper lid of the exterior 11 and the exhaust port of the air hole 14 do not malfunction due to condensation. The heater for warming the above part can also be used as a heater for preventing condensation of the pilot chute 12.

  The temperature of the heater (the temperature of the device that generated heat, the temperature of warm air, etc.) is preferably 5 ° C. or higher, more preferably 8 ° C. or higher, and even more preferably 10 ° C. or higher. When the temperature of the heater is less than 5 ° C., it tends to be difficult to prevent the occurrence of condensation. Moreover, it is preferable to manage the temperature of the heater so that the pilot chute 12 and the main parachute 13 to be used do not deteriorate due to heat.

  The heater is preferably configured to receive power supply from a power source such as a battery mounted in advance on the drone. With the above configuration, it is possible to eliminate the necessity of mounting a battery or the like on the parachute system 10 itself.

  In addition, in order to assist the function which prevents that dew condensation arises in the pilot chute 12 and the main parachute 13, it is good also as a structure which utilizes the exhaust heat of the discharge | emission control means 15. FIG.

  The predetermined condition for discharging the pilot chute 12 can be set as appropriate. Hereinafter, the predetermined conditions that can be set will be described in detail, but the predetermined conditions are not limited to the following modes.

  In the parachute system 10 according to the present embodiment, the state detection means (not shown) can detect the state of the drone in which the parachute system 10 is installed, and the state determination means (not shown) has a predetermined condition. It is preferable that the discharge control means 15 performs control to enable the pilot chute 12 to be discharged when the state satisfies a predetermined condition. With the above configuration, the pilot chute 12 and the main parachute 13 can be quickly discharged when the drone stops operating normally due to a sudden accident or the like.

  Although the kind of sensor which can be used as a state detection means is not specifically limited, For example, an altitude sensor, a 3 axis inclination sensor, a temperature sensor, a fall speed sensor, or a battery sensor etc. are mentioned.

  The altitude sensor is a sensor that can detect the altitude at which the drone is located. For example, an altitude threshold value is set in advance, and the fact that the drone has reached an altitude equal to or lower than the threshold value can be set as a predetermined condition for discharging the pilot chute 12. With the above setting, the pilot chute 12 and the main parachute 13 can be reliably discharged before the drone reaches the ground surface.

  The triaxial tilt sensor is a sensor that can detect how much the drone is tilted in the vertical direction, the horizontal direction, and the longitudinal direction. For example, the threshold value of the tilt angle is set in advance, and the state where the tilt angle is equal to or greater than the threshold value has not been maintained for a certain period of time This can be set as a predetermined condition for discharging the pilot chute 12. With the above setting, when the drone cannot fly in a normal posture, the pilot chute 12 and the main parachute 13 can be quickly discharged.

  A temperature sensor is a sensor that can detect the temperature at a location where the sensor is provided. For example, a temperature threshold is set in advance, a temperature sensor is installed in the discharge control means 15 of the parachute system 10, the control means of the drone, or a battery, and the temperature of the installation location has become a predetermined value or more. The predetermined condition for discharging the pilot chute 12 can be set. With the above setting, when an abnormality such as heat generation occurs in the parachute system 10 or the drone, the pilot chute 12 and the main parachute 13 can be quickly discharged.

  The drop speed sensor is a sensor that can detect the drop speed of the drone by detecting the distance and time that the drone has moved downward. For example, it is possible to set a threshold value for the falling speed in advance, and to set a predetermined condition for discharging the pilot chute 12 that the drone has reached a falling speed equal to or higher than the threshold value. With the above setting, when the drone starts dropping due to a sudden accident or the like, the pilot chute 12 and the main parachute 13 can be quickly discharged.

  The battery sensor is a sensor that can detect the remaining battery level of the drone. For example, a threshold value for the remaining battery level can be set in advance, and a predetermined condition for discharging the pilot chute 12 can be set when the remaining battery level falls below the threshold value. With the above setting, the pilot chute 12 and the main parachute 13 can be discharged before the drone runs out of battery.

  The sensors may be provided inside the exterior 11 or may be provided outside the exterior 11. In the case where the sensors are provided outside the exterior 11, sensors provided in the drone may be used as the sensors.

  In the parachute system 10 according to the present embodiment, the receiving means (not shown) can receive specific information from the drone in which the parachute system 10 is installed, and the state detecting means receives the specific information. Is preferably detectable as a state representing that the drone is operating normally. With the above configuration, when an abnormality occurs in the drone electrical system, the pilot chute 12 and the main parachute 13 can be quickly discharged.

  Moreover, specific information can be transmitted from the parachute system 10 to the drone, and reception of the specific information in the drone can be detected as a state indicating that the parachute system 10 is operating normally. Is preferred. With the above configuration, when an abnormality occurs in the electric system of the parachute system 10, the pilot chute 12 and the main parachute 13 can be quickly discharged.

  More specifically, the transmission / reception of specific information as described above can be performed as transmission / reception of information (survival signal) performed at regular time intervals. That is, when the state detection unit detects the transmission / reception of the survival signal and the state determination unit determines that the transmission / reception of the survival signal has not been performed for a predetermined time or longer, the discharge control unit 15 enables the pilot chute 12 to be discharged. It is preferable that the control be performed. With the above configuration, when an abnormality occurs in the electric system of the drone or the parachute system 10, the pilot chute 12 and the main parachute 13 can be quickly discharged.

  Communication such as input of information from various sensors and transmission / reception of a survival signal may be performed using either a wireless or wired method.

  In addition, a signal for instructing the opening of the drone from a controller capable of remotely operating the drone is input to the discharge control unit 15, or a signal regarding the arrival of the drone at a predetermined location is input to the discharge control unit 15. As a condition, the pilot chute 12 and the main parachute 13 may be discharged.

  A plurality of predetermined conditions as described above may be set, and the pilot chute 12 and the main parachute 13 may be discharged when any one or several conditions are satisfied.

  In addition, the parachute system 10 according to the present embodiment includes a stopping unit that stops the operation of the drone (for example, rotation of the propeller in the case of a multicopter) when the pilot chute 12 and the main parachute 13 are discharged. preferable. By providing the stopping means, the drone in which an abnormality has occurred can be landed quickly and collected.

  It is preferable that the parachute system 10 which concerns on this embodiment is provided with the binding band (not shown) which can be bound with the framework etc. which comprise a drone. By providing the binding band, the parachute system 10 can be easily installed in the drone regardless of the shape of the framework or the like. Moreover, in order to install the parachute system 10 more reliably, it is preferable to provide a plurality of binding bands. When installing the parachute system 10 in the drone, it is preferable to install the parachute system 10 so that the pilot chute 12 and the main parachute 13 are discharged upward.

  A plurality of parachute systems 10 according to the present embodiment can be attached to the drone. When a plurality of parachute systems 10 are attached, it is preferable that the parachute systems 10 are connected to each other with a dedicated communication cable so that each can be operated simultaneously. By setting it as the said aspect, it becomes possible to open the some pilot chute 12 and the main parachute 13 simultaneously.

  The present invention relates to an aircraft such as a drone equipped with a parachute system 10. In the case of an aircraft such as the drone as described above, when a sudden accident occurs, the pilot chute 12 and the main parachute 13 are reliably opened, and the aircraft can land relatively safely.

  An aircraft such as a drone may use a battery or the like as a power source, or may use a generator such as an engine, or may use a solar cell or the like that can generate solar power. There may be.

DESCRIPTION OF SYMBOLS 10 Parachute system 11 Exterior 12 Pilot chute 13 Main parachute 14 Air hole 15 Emission control means 16 Power supply connector

Claims (8)

It has a pilot chute, a main parachute, and a heater,
The pilot shoot is connected to the main parachute canopy,
A parachute system in which a heater is installed in a manner capable of preventing condensation on the pilot chute and the main parachute. With an exterior that can accommodate the pilot chute and main parachute,
The parachute system according to claim 1, wherein the exterior is composed of an aluminum heat insulating sheet. State detection means capable of detecting the state of the aircraft in which the parachute system is installed;
State determination means capable of determining whether or not the detected state satisfies a predetermined condition;
The parachute system according to claim 1, further comprising: a discharge control unit that performs control so that the pilot chute can be discharged when the state satisfies a predetermined condition. The parachute system according to claim 3, wherein the state detection means includes at least one sensor selected from the group consisting of an altitude sensor, a three-axis tilt sensor, a temperature sensor, a drop speed sensor, and a battery sensor. It is equipped with a receiving means that can receive specific information from an aircraft with a parachute system installed,
The parachute system according to claim 3 or 4, wherein the state detection means can detect reception of specific information as a state indicating that the aircraft is operating normally. An air hole and a fan capable of blowing air into the air hole;
The discharge control means performs control to operate the fan when a predetermined condition is satisfied,
The parachute system according to any one of claims 3 to 5, wherein the pilot chute is inflated and discharged by the air that has passed through the air hole. The parachute system in any one of Claims 1-6 provided with the connector for electric power supply which receives electric power supply from the electric power source of the aircraft which installed the parachute system. An aircraft comprising the parachute system according to any one of claims 1 to 7.

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