KR102549903B1 - Parachute ejection device for aircraft - Google Patents

Abstract

A parachute ejection device (1) for an aircraft according to the present invention is configured as follows. The device comprises: a guide parachute ejection unit (100) that stores a guide parachute (101) and is configured to eject the guide parachute (101) upward; and a main parachute storage unit (300) that stores a main parachute (301) connected to the guide parachute (101) and is configured to allow the main parachute (301) to be withdrawn upward along the guide parachute (101) when the guide parachute (101) is ejected upward. Therefore, there are the following effects. In order to eject and unfold the main parachute (301), which is a large parachute, upward, there is no need for a large driving unit such as a large capacity fan, and the main parachute (301) can be easily and quickly unfolded with a small fan (130) that can unfold the guide parachute (101). Therefore, since a large driving unit is not required, the present invention can be manufactured in a small, lightweight, and compact design, and thus can be easily mounted on an aircraft (D). In addition, the present invention can be mounted on various aircraft (D) such as airplanes, helicopters, etc. as well as drones to reduce the falling speed in the event of a fall due to a breakdown, collision, etc. in the air and prevent damage to the aircraft (D), thereby preventing human casualties and economic losses.

Description

Parachute ejection device for aircraft}

The present invention relates to a parachute ejection device for an aircraft, and more particularly, in order to prevent an aircraft from crashing and being damaged due to a failure, the main parachute is withdrawn while the guide parachute is discharged in an emergency so that the main parachute can be quickly and easily deployed. It relates to a parachute discharge device for an aircraft, characterized in that configured.

Hereinafter, a safety device for drones according to the background art together with the accompanying drawings will be described.

1 is described together as a front view showing that a parachute is discharged upward and unfolded due to a failure during flight after a safety device for a drone according to a background art is mounted on a drone.

A drone (1, drone) is a flying vehicle with a propeller attached to the body. It is a flying vehicle that can fly or be manned by a drone pilot.

These drones 1 are used in a variety of fields, from fighter jets to strike or spy on enemies, aerial photography, delivery as well as boarding (drone taxi).

However, such a drone 1 may fall and be damaged due to a breakdown or collision (collision with another flying vehicle or collision with a building, cliff, etc.) while flying in the air, resulting in human casualties and economic losses.

In order to solve this problem, a safety device for a drone using a parachute 10 has been suggested in prior art literature.

A launching device is configured inside the cylindrical housing, and a canopy 11 constituting the parachute 10 and a line 15 are accommodated inside the housing, and the line 15 is connected to the housing. In addition, a sensing unit, which is a sensor for detecting the danger of the drone 1, is configured, and a control unit is configured to operate the launch device to eject the canopy 11 upward after receiving a danger signal from the sensing unit. The launch device discharges the parachute 10 upward by expanding the compressed spring or by exhausting the compressed gas.

After installing such a safety device for drones on the drone 1, while flying in the air, the vibration, impact force, or tilt changes due to self-failure or collision, so when danger is detected by the sensing unit, a danger signal is transmitted to the control unit. . In addition, the control unit operates the launch device so that the parachute 10 is discharged upward and unfolds, thereby reducing the fall speed of the drone 1 to prevent damage due to collision with the ground.

By the way, the drone safety device can be applied to the small drone 1, but there is a problem in that it cannot be used in the case of a large drone used for boarding or moving heavy cargo to be used for delivery.

The large drone weighs from 100 kg to 300 kg, and accommodates a large parachute having a larger volume than the parachute 10 so as to withstand the weight when falling in the air. However, these large parachutes are folded and stored inside the drone, but in order to properly unfold them in an emergency, the capacity of the launching device must be increased compared to the existing ones. However, when the capacity of the launcher is increased in this way, the size and weight increase and the energy to be driven increases, so there is a problem in that it cannot be mounted on the drone. That is, since the size and weight of the launching device and the energy storage device (storage battery or gas cylinder) increase, a problem that makes flight difficult due to the increased weight of the drone occurs.

In addition, these safety devices for drones can be prepared for emergency situations when applied to various flying vehicles such as airplanes and helicopters in addition to drones, but as mentioned above, it is not applied due to the absence of technology that can quickly and easily eject and unfold large parachutes. It is currently not possible.

(Document 1) Korean Patent Publication No. 10-2020-0073546 (June 24, 2020) (Document 2) Korean Patent Publication No. 10-2022-0061605 (May 13, 2022)

Problems to be solved through the parachute ejection device for an aircraft according to the present invention are as follows.

It is possible to have a compact design that is small and lightweight so that it can be mounted on various aircraft such as airplanes and helicopters as well as drones, and it is configured to easily and quickly eject and unfold a large parachute that can withstand the heavy weight of the aircraft. In the case of a fall due to a collision or the like, the fall speed is reduced to prevent damage to the aircraft. Therefore, the purpose of the present invention is to provide technology that can prevent human accidents and economic losses.

Parachute discharge device for aircraft according to the present invention is configured as follows in order to solve the above problems.

A guide parachute is accommodated, a guide parachute discharge unit configured to discharge the guide parachute upward, and a main parachute connected to the guide parachute are stored. When the guide parachute is discharged upward, the main parachute is and a main parachute storage unit configured to be drawn upward along the induction parachute.

In addition, a casing opened upwards for accommodating the induction parachute discharge unit and the main parachute storage unit may be further included.

In addition, when the casing is not configured, the main parachute accommodating part is formed with an open portion to accommodate the main parachute, and when the induction parachute is discharged upward, the induction parachute is tensioned and the opening portion rotates upward. In order to do so, it may include a container configured to be mounted on an aircraft.

In addition, when the casing is configured, the main parachute accommodating part has an opening formed on one side to accommodate the main parachute, and when the induction parachute is discharged upward, the induction parachute is tensioned and the opening part rotates upward. To do so, it may include a container mounted inside the housing.

In addition, the induction parachute discharge unit may include the following configuration.

It may include a pipe-shaped housing and a fan mounted on the housing to discharge the guide parachute.

The housing may include a blow pipe disposed inside the housing and above the fan, and a flange formed along a circumference of an end of the blow pipe toward the fan and connected to an inner surface of the housing.

The induction parachute may be accommodated in a storage space between the air blow pipe and the housing in a state in which the air blow pipe is covered.

According to the present invention by the above solution, the following effects are obtained.

The present invention does not require a large drive unit such as a large-capacity fan to discharge and open the main parachute, which is a large parachute, in an upward direction. It works. Therefore, since the large driving unit is not required, the present invention can be manufactured in a small, lightweight and compact design, and this is an effect that can be easily mounted on an aircraft.

In particular, since the container is not erected and rotates to lie down, it is possible to prevent the phenomenon of protruding upward, thereby preventing the phenomenon of causing air resistance during flight, and to rotate upward in an emergency, so that it can be easily It has the effect of allowing the main parachute to be drawn upward and unfolded.

Therefore, it is installed on various high-weight vehicles such as airplanes and helicopters as well as drones to prevent damage to the aircraft by reducing the fall speed when it crashes or crashes in the air, thereby preventing human accidents and economic losses. It works.

1 is a front view showing that a parachute is discharged upward and unfolded due to a failure during flight after a safety device for a drone according to a background art is mounted on a drone.
Figure 2 is a longitudinal cross-sectional view showing a parachute discharge device for an aircraft according to the present invention.
Figure 3 is a longitudinal cross-sectional view showing a process in which the guidance parachute starts to be discharged upward in an emergency in the state of Figure 2;
Figure 4 is a longitudinal cross-sectional view showing an operating process in case of an emergency, separately extracted from the guide parachute discharge unit in Figure 3;
Figure 5 is a parachute discharge device for an aircraft according to the present invention, a perspective view showing the main parachute omitted.
6 is a perspective view showing a state in which a casing in which a main parachute is accommodated is rotated upward in the state of FIG. 5;
7 is a longitudinal cross-sectional view taken along line F-F' of FIG. 6;
8 is a longitudinal cross-sectional view showing a process of withdrawing the main parachute upward after the guide parachute is discharged upward in the state of FIG. 3;
9 is a longitudinal cross-sectional view showing a completely unfolded state by withdrawing the main parachute upward while the guide parachute is discharged upward and unfolded as a parachute discharge device for an aircraft according to the present invention.
Figure 10 is a front view showing a state in which the parachute is discharged upward and unfolded in an emergency during flight in a state in which the parachute discharge device for an aircraft according to the present invention is mounted on the aircraft.
Figure 11 is a block diagram showing a control unit configured in the parachute ejection device for an aircraft according to the present invention to operate after detecting an emergency state.

Hereinafter, various embodiments of this document will be described with reference to the accompanying drawings. However, this is not intended to limit the technology described in this document to specific embodiments, and is to be understood as including various modifications, equivalents, and/or alternatives of the embodiments of this document. In connection with the description of the drawings, like reference numerals may be used for like elements.

In addition, expressions such as “first,” “second,” etc. used in this document may modify various components regardless of order and/or importance, and to distinguish one component from another. It is used only and does not limit the corresponding components. For example, 'first part' and 'second part' may indicate different parts regardless of order or importance. For example, without departing from the scope of rights described in this document, a first element may be called a second element, and similarly, the second element may also be renamed to the first element.

In addition, terms used in this document are only used to describe a specific embodiment, and may not be intended to limit the scope of other embodiments. Singular expressions may include plural expressions unless the context clearly dictates otherwise. Terms used herein, including technical or scientific terms, may have the same meaning as commonly understood by a person of ordinary skill in the technical field described in this document. Among the terms used in this document, terms defined in a general dictionary may be interpreted as having the same or similar meaning as the meaning in the context of the related art, and unless explicitly defined in this document, an ideal or excessively formal meaning. not be interpreted as In some cases, even terms defined in this document cannot be interpreted to exclude the embodiments of this document.

Hereinafter, a detailed embodiment of the parachute discharge device 1 for an air vehicle according to the present invention together with the accompanying drawings will be described.

Figure 2 is a longitudinal cross-sectional view showing a parachute discharge device for an aircraft according to the present invention, Figure 3 is a longitudinal cross-sectional view showing a process in which the guidance parachute starts to be discharged upward in an emergency in the state of FIG. In addition, Figure 4 is a longitudinal cross-sectional view showing an operating process in an emergency by extracting the guide parachute discharge unit separately from Figure 3, and Figure 5 is a parachute discharge device for an air vehicle according to the present invention, a perspective view showing the main parachute omitted. am. In addition, FIG. 6 is a perspective view showing a state in which the casing in which the main parachute is accommodated is rotated upward in the state of FIG. 5, and FIG. 7 is a longitudinal cross-sectional view taken along the line F-F' of FIG. In addition, Figure 11 will be described together as a block diagram showing a control unit configured in the parachute ejection device for an air vehicle according to the present invention to operate after detecting an emergency state.

As shown in FIG. 2, the induction parachute 101 is accommodated, and the induction parachute discharge unit 100 discharging the induction parachute 101 upward is configured. In addition, the main parachute 301 connected to the induction parachute 101 is accommodated, so that the main parachute 301 can be drawn upward along the induction parachute 101 when the induction parachute 101 is discharged upward. The parachute storage unit 300 is configured.

The induction parachute discharge unit 100 and the main parachute storage unit 300 may be mounted by providing a storage space directly to various flying objects such as drones, helicopters, and airplanes, and as shown in FIG. 2, the casing 400 opened upwards It may be mounted in the storage space in a state accommodated in the interior of.

The configuration of the induction parachute discharge unit 100 is as follows with reference to FIGS. 2 to 4 .

The induction parachute 101 is in the form of a sheet, and includes a canopy 103 that receives air resistance during descent, and includes a plurality of lines 105 connected along the outer circumference of the canopy 103, and a plurality of lines 105. A riser 107, which is a belt or rope connected by gathering 105, is constituted.

In addition, a pipe-shaped housing 120 in which the induction parachute 101 is accommodated is configured. When the casing 400 is not configured, the lower end is fixed to the aircraft D, and when the casing 400 is configured, the lower end is fixed. It is fixed to the inner lower surface of the casing 400. In addition, a fan 130 mounted on the housing 120 to discharge the guide parachute 101 upward is built-in.

Inside the housing 120, an air blow pipe 140 penetrating up and down through the top of the fan 130 is disposed, and is formed along the circumference of the end of the air pipe 140 toward the fan 130 so that the housing 120 A flange 145 connected to the inner surface of is configured. Accordingly, a storage space 150 open upward is formed between the housing 120 and the air blow pipe 140 .

The induction parachute 101 is constructed by being accommodated in the storage space 150 together with an umbrella line 105 in a state where the canopy 103 covers the blowing pipe 140. At this time, the riser 107 is drawn out and connected to the main parachute 301.

The upper end of the housing 120 is covered with a cap 160 to prevent foreign matter from being accommodated, and is configured to be easily removed when the canopy 103 is discharged upward. That is, when the fan 130 is driven, as shown in FIGS. 3 and 4, the canopy 103 is configured to push the cap 160 upward while inflating upward like a balloon and starting to be discharged. However, when the present invention is mounted inside the aircraft (D), an embodiment in which the cap 160 is not configured is also possible.

In addition, the housing 120 is configured such that an inlet 127 is formed at the bottom of the fan 130 so that external air can be easily introduced when the fan 130 is driven. As another example, since the inlet 127 is not formed and a plurality of legs (not shown) are mounted on the lower end of the housing 120 and fixed to the inner lower surface of the aircraft D or casing 400, it passes between the legs. Air may be introduced into the lower part of the housing 120 . In addition, when the casing 400 is configured, a through hole (not shown) may be formed in the casing 400 to facilitate the inflow of air.

The configuration of the main parachute storage unit 300 will be described in conjunction with FIGS. 2, 3, and 5 to 9.

The main parachute 301 is larger in size than the induction parachute 101 and is configured to sufficiently reduce the fall speed of the heavy aircraft D. The main parachute 301 is in the form of a sheet, and includes a canopy 303 that receives air resistance during descent, and includes a plurality of lines 305 connected along the outer circumference of the canopy 303, and a plurality of lines 305. A riser 307, which is a belt or rope connected by gathering 305, is constituted.

In addition, a storage box 310 having an opening 315 formed on one side is configured to accommodate the main parachute 301, so that the canopy 303 is stored in a folded state, and the sunshade 305 and the riser 307 are also The riser 307 is configured to pass through the storage box 310. When the casing 400 is configured, the casing 400 is also configured to pass through. Therefore, when mounted on the aircraft (D) later, when mounted on the aircraft (D) directly without the casing 400, the riser 307 passes through the container 310 and is directly connected to the aircraft (D), the casing When the 400 is configured, it passes through the housing 310 and the casing 400 at the same time and is configured to be connected to the aircraft (D). In addition, the container 310 is configured to rotate directly to the aircraft D in an embodiment in which the casing 400 is not configured, and in the case where the casing 400 is configured, the casing 400 as shown in FIGS. 5 to 7 It is supported and configured to rotate on. At this time, the container 310 is in a state of being rotated so that the opening 315 faces the guide parachute discharge unit 100 in a state where the main parachute 301 is stored. Therefore, when the induction parachute 101 is discharged upward, the storage container 310 rotates upward and the opening 315 faces upward so that the main parachute 301 can be easily withdrawn upward. .

As an example, a shaft (not shown) is fixed to the left and right sides of the storage box 310 in order to be mounted so that the storage box 310 rotates directly on the aircraft D, and the shaft is fixed to the aircraft D. It is possible because it is combined with a bearing (not shown).

When the container 310 is mounted to rotate in the casing 400, a shaft (not shown) penetrates the casing 400 and the container 310 at the same time, so that the container 310 may be rotated. 7, it may be possible because the rotation part 320 is further configured to connect both sides of the container 310 and both sides of the casing 400 so as to mutually rotate.

As an example, the pivoting part 320 includes a single hole 321 passing through both sides of the container 310 and a plurality of tap holes 322 passing around each hole 321 . Next, holes 323 corresponding to the holes 321 pass through both sides of the casing 400, and a plurality of tap holes 324 pass through the circumference of the hole 323 to correspond to the tap holes 322. is made up of Next, a water fitting 325 inserted into either one of the holes 321 and 323 on both sides is configured, and an arm fitting 327 inserted into the other side and coupled to the water fitting 325 is configured.

The water fitting 325 is composed of a shaft F passing through the holes 321 and 323 at the same time and a plate-shaped head H1 connected to one end of the shaft F, and the head H1 has A screw hole W1 corresponding to one of the tap holes 322 and 324 and serving as a through hole is formed. Further, a screw S1 passing through the screw hole W1 and fastened to one of the tap holes 322 and 324 is configured.

The arm fastening hole 327 passes through the holes 323 and 321 at the same time, and constitutes an insertion tube P into which the shaft F is inserted, and a plate-shaped head connected to one end of the insertion tube P. (H2) is configured, and a screw hole (W2) corresponding to any one of the tap holes (322, 324) and being a through hole is formed in the head (H2). Further, a screw S2 passing through the screw hole W2 and fastened to one of the tap holes 322 and 324 is configured.

Therefore, after passing the female fastener 327 through one of the holes 321 and 323 on both sides, the screw S2 passes through the screw hole W2 and is fastened to one of the tap holes 322 and 324, 325 is passed through the opposite side of the holes 321 and 323 on both sides to insert the insertion tube P into the inside. Then, the screw S1 passes through the screw hole W1 and is fastened to the other side of the tap holes 322 and 324.

Therefore, since mutual rotation is possible in the state where the shaft (F) is inserted into the insertion tube (P), the storage tube (310) is configured to be able to rotate.

In addition, as shown in FIG. 11, a sensing unit 510 is installed on the parachute discharge device 1 for an air vehicle or the air vehicle D according to the present invention and detects the fall of the air vehicle D and transmits a signal. A controller 520 receives a signal from the unit 510 and supplies electricity to the fan 130 . Electricity at this time may be supplied from the battery of the aircraft (D), or may be supplied with a separate battery.

As an example, the sensing unit 510 may be selectively configured among an acceleration sensor, a gyro sensor, a vibration sensor, an impact sensor, and an air pressure sensor. That is, when the acceleration sensor detects the gravitational acceleration generated when the vehicle D is falling, it detects it as a failure and transmits a signal to the control unit 520. In addition, the gyro sensor transmits a signal to the controller 520 by detecting that the vehicle D is tilted at a predetermined angle or more. In addition, the vibration sensor and the shock sensor detect vibration and shock generated when the aircraft D collides with a multi-FMS aircraft or a building or a cliff, respectively, and transmits a signal to the control unit 520. In addition, the air pressure sensor transmits a signal by detecting a sudden change in air pressure when the aircraft D crashes. In addition, in the present invention, all sensors capable of detecting the fall of the vehicle D may be configured as the sensing unit 510.

The control unit 520 can receive the signal and conduct electricity to the fan 130, such as a CPU (Central Processing Unit), a PCB (Printed Circuit Board), or a switch, for example.

In the above, the operating process of the parachute discharge device 1 for an air vehicle according to the present invention looked at together with the accompanying drawings will be described.

2 is a longitudinal cross-sectional view showing a parachute discharge device for an aircraft according to the present invention, and FIG. 3 is a longitudinal cross-sectional view showing a process in which a guide parachute starts to be discharged upward in an emergency in the state of FIG. 2, and FIG. In FIG. 3, the guide parachute discharge part is separately extracted and is a longitudinal cross-sectional view showing an operation process in case of emergency. 8 is a longitudinal cross-sectional view showing a process of withdrawing the main parachute upward after the guidance parachute is discharged upward in the state of FIG. 3, and FIG. It is a longitudinal cross-sectional view showing the completely unfolded state by withdrawing the main parachute upward as it is discharged and unfolded. In addition, Figure 10 is a front view showing a state in which the parachute is discharged upward and unfolded in an emergency during flight in a state where the parachute discharge device for an aircraft according to the present invention is mounted on the aircraft, and Figure 11 is a parachute for an aircraft according to the present invention It is a block diagram showing a control unit configured in the discharge device to operate after detecting an emergency state.

As shown in FIG. 2 , in a state in which the opening 315 of the container 310 is rotated toward the housing 120, the riser 307 of the main parachute 301 moves the container 310 and the casing 400 ) and is connected to the aircraft (D). In an embodiment in which the casing 400 is not configured, the riser 307 passes through the container 310 and is directly connected to the aircraft D. At this time, since the container 310 rotates sideways to lie down, there is an advantage in that it can be easily accommodated in the aircraft D. If it is in a standing state without turning, since it protrudes upward from the aircraft D, a problem in that air resistance increases during flight occurs and a problem in which the appearance is not beautiful occurs.

While flying while being mounted on the aircraft D, the moment when a failure occurs or the aircraft D crashes due to a crash, the sensing unit 510 detects this and transmits a signal to the control unit 520. Then, the controller 520 conducts electricity to the fan 130 . Then, as shown in FIGS. 3 and 4, the fan 130 rotates and air is injected downward through the blower pipe 140. As a result, the canopy 103 of the induction parachute 101 is inflated upward like a balloon, capping the cap. (160) and starts to be discharged upwards.

In this state, when the induction parachute 101 is fully opened upward as shown in FIG. 8, the riser 107 connected to the induction parachute 101 tensions the main parachute 301 upward. Therefore, the storage container 310 of the main parachute storage part 300 is rotated upward by the tensile force so that the opening 315 is directed upward so that the main parachute 301 can be easily withdrawn upward. becomes

In this way, the induction parachute 101 pulls the canopy 303 of the main parachute 301 upward while receiving air resistance, and the flight body D is forced downward by gravity, so as shown in FIG. 9, the main parachute 301 The canopy 303 of ) is drawn upward and spreads, and the riser 307 supports the aircraft D.

Therefore, since the guide parachute 101, which is smaller in size than the main parachute 301, is discharged by the fan 130, the main parachute 301 can be easily unfolded by the air resistance of the guide parachute 101 and the weight of the aircraft D. can

According to the present invention discussed above, in order to discharge and unfold the main parachute 301, which is a large parachute, a large driving unit such as a large-capacity fan is not required, and a small fan 130 capable of unfolding the induction parachute 101 Even with this, the main parachute 301 can be opened easily and quickly. Therefore, since the large driving unit is not required, the present invention can be manufactured in a small and lightweight compact design, and this point is an advantage that can be easily mounted on the aircraft (D).

In particular, since the container 310 is not erected and rotates to lie down, it is possible to prevent the phenomenon of protruding upward, which causes air resistance during flight, and rotates upward in case of emergency. Therefore, there is an advantage in that the main parachute 301 is easily drawn upward and unfolded.

Therefore, when it is mounted on various flying vehicles (D) of high weight, such as airplanes and helicopters, as well as drones, the fall speed is reduced in the event of a fall due to a breakdown or collision in the air, thereby preventing damage to the flying body (D). Economic losses can be prevented.

1: parachute discharge device for aircraft 100: guided parachute discharge unit
101: guided parachute 103: canopy
105: line 107: riser
120: housing 127: inlet
130: fan 140: blower pipe
145: flange 150: storage space
160: cap 300: main parachute storage unit
301: main parachute 303: canopy 305: sunshade 307: riser 310: storage box 315: opening
321: hole 322: tapped hole
323: hole 324: tapped hole
325: water fitting H1: head
W1: threaded hole F: shaft
S1: screw 327: arm fastener
H2: head W2: screw hole
P: insertion tube S2: screw
400: casing 510: sensing unit
520: control unit D: aircraft

Claims (6)

delete delete A guide parachute discharge unit configured to accommodate a guide parachute and discharge the guide parachute upward;
A main parachute accommodating a main parachute connected to the induction parachute, including a main parachute accommodating portion configured to allow the main parachute to be drawn upward along the induction parachute when the induction parachute is discharged upward;
The main parachute storage unit,
An opening is formed on one side to accommodate the main parachute, and when the induction parachute is discharged upward, it is tensioned in the induction parachute and includes a storage box configured to be mounted on the aircraft so that the opening rotates upward. A parachute ejection device for an air vehicle.
A guide parachute discharge unit configured to accommodate a guide parachute and discharge the guide parachute upward;
a main parachute accommodating unit configured to accommodate a main parachute connected to the induction parachute and to allow the main parachute to be drawn upward along the induction parachute when the induction parachute is discharged upward;
It includes a casing opened upwards for accommodating the induction parachute discharge unit and the main parachute storage unit,
The main parachute storage unit,
An opening is formed on one side to accommodate the main parachute, and when the induction parachute is discharged upward, it is tensioned in the induction parachute so that the opening portion rotates upward. A parachute discharge device for an aircraft, characterized in that.
According to claim 3 or 4,
The induction parachute discharge unit,
A pipe-shaped housing;
A fan mounted on the housing to discharge the guiding parachute upward;
the housing,
A blower pipe disposed above the fan inside the housing;
A flange formed along a circumference of an end of the fan side of the blower pipe and connected to an inner surface of the housing,
The induction parachute,
Parachute discharge device for an air vehicle, characterized in that accommodated in the storage space between the air blow pipe and the housing in a state of covering the air blow pipe.
According to claim 5,
A sensing unit mounted on the parachute ejection device for the air vehicle or the air vehicle and transmitting a signal by detecting the fall of the air vehicle;
A parachute discharge device for an air vehicle, characterized in that it comprises a control unit for receiving the signal from the sensing unit and supplying electricity to the fan.

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