KR101913688B1 - Apparatus for deploying wing and flight vehicle having the same - Google Patents

Abstract

According to an embodiment of the present invention, an apparatus for deploying a wing of an aerial vehicle comprises: a separation tool where a parachute structure is connected; and a wing deployment unit where the separation tool is connected to be separated, connected to each front wing and a rear wing of the aerial vehicle, and deploying the front wing and the rear wing in accordance with resistance of the parachute structure.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to a wing-

BACKGROUND OF THE INVENTION Field of the Invention [0001] The present invention relates to an apparatus for deploying a blade and a flight body having the blade, and more particularly, to a blade deployment apparatus for flying a flight after being dropped by an aircraft or a rocket and a flight body having the blade.

Generally, a small aircraft is mounted on an aircraft or a rocket, and is dropped into the air from an airplane or a rocket in flight, and then performs air flight toward the target point. Conventional small airplanes wait for airplanes or rockets to be loaded with space before they are released into the air. In particular, the long-haul small-sized aircraft is manufactured in the form of a tandem wing, which is a main wing in both front and rear, in order to secure the wing area. In order to prevent the flying body from being excessively unstable in the longitudinal direction during the wing deployment, Must remain the same. In addition, when a long-haul small-sized aircraft is dropped into the air from an aircraft or a rocket, a deceleration chute is required for proper deceleration and posture stabilization.

Conventional long-haul-type small-sized airplanes are equipped with individual devices for blade deployment, deployment of decelerated parachute, and deceleration parachute separation. In addition, conventionally, a separate electric motor or a spring device for deployment has been required in order to deploy the wing of a flight vehicle.

The conventional wing expansion device is mainly used for deploying only a pair of wings. It can be applied only when the wing of the airplane is located in a pair of right and left sides, or in a place of a flight, and the wing tandem wings It is not possible to develop. For example, when the wings are located at two or more places in front of and behind the airplane, the wings must be deployed at the same time. In the conventional wing deployment apparatus, the speed at which each wing is deployed may be different, Resulting in an imbalance.

In addition, a conventional long-haul-type small-sized airplane is required to stabilize its posture and reduce its speed to an appropriate level by using a parachute immediately after being dropped from an airplane or a rocket, and when the speed reaches a predetermined speed, the parachute must be separated, A separate electric signal generating device and the like were required.

As described above, conventionally, the apparatus for separating the parachute and the vane-spreading device are separately provided, which increases the weight of the airplane and increases the internal space of the airplane.

Korean Patent No. 10-1117102

SUMMARY OF THE INVENTION Accordingly, the present invention has been made keeping in mind the above problems occurring in the prior art, and it is an object of the present invention to provide a vane deployment device capable of decelerating through a parachute structure, separating a parachute structure at a proper speed, The purpose is to provide a flight.

According to an aspect of the present invention, there is provided an apparatus for deploying an airplane vane, comprising: a separation mechanism to which a parachute structure is connected; And a vane deployment unit detachably connected to the separation mechanism, the vane deployment unit being connected to each of a front wing and a rear wing of the air vehicle, and deploying the front wing and the rear wing in accordance with the resistance of the parachute structure.

The vane expanding portion includes a receiving portion having one end opened and having an opening and receiving the separating mechanism through the opening, a rod portion having one end connected to the other end of the receiving portion and the other end connected to the front wing, And the rear wing is connected to the vertical shaft portion by a rear pulling rod.

The receiving portion may be formed with a through hole such that at least a part of the holding member for fixing the separating mechanism in the receiving portion is located.

Wherein the separation mechanism includes a connection portion to which the parachute structure is connected, a hollow tube portion to be coupled with the connection portion, and a fixing pin portion provided inside the hollow tube portion, the hollow tube portion being penetrated by the fixing member, And can be fixed to the inside of the accommodating portion by locating at least a part of the fixing member in the through hole while the fixing member is in close contact with the fixing pin portion.

Wherein the connection portion includes a pressing member to which the parachute structure is connected and a cylindrical portion that is formed to surround the hollow tube portion and the fixing pin portion and is open at both ends,

A ring member may be formed on the inner circumferential surface of the cylindrical portion.

Wherein the hollow tube portion has a protruding ring portion formed on the outer periphery of the center portion,

A gap retaining portion may be provided between the protruding ring portion and the ring member.

The hollow tube portion may have a support portion formed on an outer periphery of one end thereof, and a first spring may be provided between the support portion and the ring member.

The hollow tube portion may have a first inner space and a second inner space having a larger volume than the first inner space, and a second spring may be provided in the second inner space so as to surround the fixing pin portion.

The first spring may have a greater elastic restoring force than the second spring.

The fixing pin portion may have a receiving groove formed on an outer circumference thereof and the hollow tube portion may be unfixed from the receiving portion when the fixing member is received in the receiving groove.

A rear rotation shaft to which the rear wing is rotatably connected, a rotation shaft fixing unit provided on the same axis as the rear rotation shaft, and a plurality of bearings disposed to be stacked with the rear wing interposed therebetween And a rear rotating shaft portion for rotating the rear rotating shaft.

The front wing may further include a front rotation shaft to which the front wing is rotatably connected, and the front wing may be connected to the rod portion by a front pulling rod.

According to an aspect of the present invention, there is provided a flight body including a blade deployment device, A blade deploying device provided on the flying body; A parachute structure connected to the vane deployment device; A front blade rotatably connected to the front of the flying body; A rear blade rotatably connected to the rear of the flying body; And a propeller provided at the rear of the flying body to provide a propulsion force to the flying body.

The propeller unit includes a frame structure provided in the flying body, a driving shaft connected to the power unit of the flying body through the frame structure, a propeller body rotatably connected to the driving shaft, And a pair of wings connected to each other.

Therefore, according to the vane-spreading device and the flight vehicle having the vane-spreading device according to the embodiment of the present invention, since the front blades and the rear blades are disposed in a folded state, the volume is reduced, thereby easily securing a space for mounting an aircraft or a rocket.

In addition, when dropped from an aircraft or a rocket, it can be decelerated through the parachute structure to stabilize the posture, and the parachute structure can be separated at a proper speed.

 In addition, since the front wing and the rear wing are both in the form of a main wing, a tandem wing is used. If the deployment speed is different, the posture of the main body of the flying body may become unstable. The front wing and the rear wing are simultaneously deployed The posture becomes stable.

In addition, the flight vehicle can operate the blade deploying device through the resistance generated in the parachute structure without a separate control signal, thereby enhancing the reliability of the entire system.

FIG. 1 is a perspective view illustrating a blade development process of a flight vehicle having a blade expansion device according to an embodiment of the present invention.
FIG. 2 is a partially enlarged view of a flying body provided with the blade expanding device of FIG. 1;
FIG. 3 is a partially exploded perspective view of a flying body provided with the blade expanding device of FIG. 2. FIG.
4 is a sectional view of a separating mechanism and a blade expanding part according to an embodiment of the present invention.
FIG. 5 is a view for explaining a blade expanding process by the separating mechanism and the blade expanding unit of FIG. 4;
FIG. 6 is a view for explaining the separation process of the separation mechanism of FIG. 5; FIG.
FIG. 7 is a partial plan view of the airplane provided with the vane deployment device according to the embodiment of the present invention, and FIG. 7 (a) As shown in FIG.
FIG. 8 is a partial plan view of the airplane with the vane deployment device according to the embodiment of the present invention developed after the air vane has been deployed. FIG. 8 (a) As shown in FIG.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. In the drawings, the same reference numerals are used to designate the same or similar components throughout the drawings. In addition, the preferred embodiments of the present invention will be described below, but it is needless to say that the technical idea of the present invention is not limited thereto and can be variously modified by those skilled in the art.

Referring to FIG. 1, a flight body 10 having a vane deployment device according to an embodiment of the present invention is a plane body 100, a vane deployment device 200 , A parachute structure 300, a front wing 400, a rear wing 500, a propeller portion 600, and a search device 700.

The flight main body 100 is equipped with various devices necessary for flight. The vane deploying device 200 is provided at the rear of the flight main body 100. The parachute structure 300 is connected to the vane deployment device 200. The front wing 400 is pivotally connected to the front of the flying body 100. The rear wing 500 is pivotally connected to the rear of the flying body 100. The propeller unit 600 is provided at the rear of the flying body 100. The search device 700 is provided in front of the flying body 100.

In the air vehicle 10 according to the embodiment of the present invention configured as described above, the front blades 400 and the rear blades 500 are normally folded on the upper and lower portions of the flight main body 100, respectively. When the air vehicle 10 is dropped into the air, the parachute structure 300 is deployed and the blade expansion device 200 is operated by the resistance of the parachute structure 300. At this time, the vane deployment device 200 deploys the front vane 400 and the rear vane 500 at the same time. The vane deployment device 200 separates the parachute structure 300 when the front vane 400 and the rear vane 500 are fully deployed. Thereafter, the propeller unit 600 of the air vehicle 10 is operated, and it is possible to fly the air toward the target point through the propulsive force generated by the propeller unit 600. Here, the target point search and tracking is possible by the search device 700.

Therefore, since the front wing 400 and the rear wing 500 are arranged in a folded state, the volume of the air body 10 is reduced, thereby ensuring a space for mounting the aircraft or the rocket It is easy.

In addition, when the airplane 10 is dropped from an aircraft or a rocket, the airplane 10 can be decelerated through the parachute structure 300 to stabilize the posture and separate the parachute structure at a proper speed.

In addition, since the front wing 400 and the rear wing 500 are both in the form of a tandem wing having a main wing shape, the flying body 10 may be unstable when the deployment speed is different Since the front blades 400 and the rear blades 500 can be deployed at the same time through the blade expansion device 200, the posture is stabilized.

In addition, the air vehicle 10 can operate the vane expander 200 through the resistance generated in the parachute structure 300 without a separate control signal, thereby enhancing the reliability of the entire system.

Hereinafter, the configuration of the air vehicle 10 having the vane-spreading device according to the embodiment of the present invention will be described in detail.

The flying body 100 may be formed to have a rectangular rod shape, but is not limited thereto. The interior of the flight body 100 may be hollow. A power unit for transmitting power to the propeller unit 600 and a connecting member for connecting the blade unit 200 and the front blades 400 may be provided in the interior of the flying body 100.

The vane deploying device 200 is provided at the rear of the flight main body 100. The vane deploying apparatus 200 is connected to the parachute structure 300, the front vane 400, and the rear vane 500. The vane deployment device 200 may separate the parachute structure 300 when the flight body 100 is released into the air. Also, the vane deployment device 200 can be deployed at the same time by rotating the front vane 400 and the rear vane 500. The detailed configuration of the vane spread device 200 will be described later with reference to Figs. 3 to 6. Fig.

The parachute structure 300 may comprise a hemispherical body and a plurality of straps connected to the periphery of the body. The parachute structure 300 is configured such that a plurality of straps meet at one point. The parachute structure 300 is connected to the vane deployment device 200 via a connecting strap 210. An air hole is formed in the body of the parachute structure 300, so that the air escapes through the air hole and is spread in the form of a hemisphere in the air. The parachute structure 300 generates a resistance force on the inner circumferential surface due to the wind, and through this resistance force, the deceleration of the flying body 100 and the operation of the blade expanding apparatus 200 are possible.

The front wing 400 is pivotally connected to the front of the flying body 100. The front wing 400 may be in the form of a tandem wing. The front wing 400 includes a left front wing 410 and a right front wing 420.

The left front wing 410 and the right front wing 420 are folded at the top of the flying body 100 in a flat state. The left front wing 410 and the right front wing 420 are deployable by the vane deployment device 200. The left front wing 410 is deployed vertically from the left side of the flight body 100 when deployed by the vane deployment device 200. The right front blades 420 are arranged to extend vertically from the right side of the flight body 100 when they are deployed by the vane deployment device 200. The left front wing 410 and the right front wing 420 generate a lift near the front of the flying body 100 to balance the rear wing 500 and enable stable flight of the flying body 100.

The rear wing 500 is pivotally connected to the rear of the flying body 100. The rear wing 500 may be in the form of a tandem wing. The rear blade 500 has a wing control surface capable of adjusting a part of the back surface of the wing to a specific vertical angle. The blade control surface of the rear blade 500 can control the posture and the traveling direction of the air vehicle 10. The rear wing 500 includes a left rear wing 510 and a right rear wing 520.

The left rear wing 510 and the right rear wing 520 are disposed at the bottom of the flying body 100 in a flat state. The left rear blade 510 and the right rear blade 520 are deployable by the vane deployment device 200. The left rear wing 510 is deployed vertically from the left side of the flight body 100 when deployed by the vane deployment device 200. Also, the right rear blade 520 is arranged to extend vertically from the right side surface of the flying body 100 when it is deployed by the vane deployment device 200. The left rear wing 510 and the right rear wing 520 generate lift in the vicinity of the rear of the flying body 100 to enable stable flight of the flying body 100. [

2 and 3, the left rear blade 510 and the right rear blade 520 may be equipped with servo control devices 511 and 521 for controlling the blade control surfaces, respectively. The servo control units 511 and 521 can determine the angles of the blade control surfaces of the left rear blade 510 and the right rear blade 520 according to the control command.

Referring again to FIG. 1, the propeller unit 600 is provided at the rear of the flying body 100. The propeller unit 600 may provide a propulsive force to the flight body 100. The propeller unit 600 preferably operates when the parachute structure 300 is disconnected.

2 and 3, the propeller unit 600 may include a frame structure 610, a drive shaft 620, a propeller body 630, and a pair of blades 640.

The frame structure 610 is provided at the rear of the flying body 100. The frame structure 610 may be constructed through a combination of a plurality of horizontal members horizontal to the rear surface of the flying body 100 and a plurality of vertical members perpendicular to the rear surface of the flying body 100. The frame structure 610 may have a through hole formed in the horizontal member. The drive shaft 620 may be inserted into the through hole of the frame structure 610.

 The drive shaft 620 may pass through the rear surface of the flying body 100 and may be connected to a power unit (not shown). The drive shaft 620 can be rotated by the power of the power unit. The drive shaft 620 can transmit rotational force to the propeller body 630. Here, the power unit may be an electric motor, a reciprocating engine, or the like. It is also desirable that the power unit operate when the parachute structure 300 is separated by the vane deployment device 200.

The propeller body 630 may be rotatably connected to the drive shaft 620. The propeller body 630 is formed in a rod shape, but is not limited thereto. At both ends of the propeller body 630, a pair of blades 640 are provided.

A pair of blades 640 are pivotally connected to the propeller body 630. The pair of wings 640 are normally arranged in a folded state so as to face the frame structure 610. The pair of wings 640 is arranged to be in line with the propeller body 630 when the propeller body 630 is rotated by its centrifugal force. The pair of blades 640 can rotate together with the propeller body 630 to generate propulsive force. The pair of wings 640 provide the above-mentioned propulsive force to the flying body 100.

Hereinafter, the configuration of the vane-spreading device 200 according to the embodiment of the present invention will be described in detail with reference to FIG. 3 and FIG.

The blade expansion device 200 includes a separation mechanism 210, a blade expansion unit 220, a gap holding unit 230, a rear rotation axis unit 240, a rear pulling rod 250, a front rotation axis unit 260, And may include a rod 270.

The separation mechanism 210 is for separating the parachute structure 300 from the flight main body 100 and may include a connecting portion 211, a hollow tube portion 213, a fixing pin portion 215, and a fixing cap 217 have.

The connecting portion 211 may include a pressing member 211a to which the parachute structure 200 is connected and a cylindrical portion 211b having both ends thereof connected to the pressing member 211a.

The pressing member 211a may be a cylindrical shape having one end opened and an opening, but is not limited thereto. A hook may be formed at the other end of the pressing member 211a. The connection string 210 of the parachute structure 200 may be connected to the loop of the pressure member 211a. Here, the connection structure of the pressing member 211a and the parachute structure 200 is not limited to the above example, but may be formed in various ways.

The cylindrical portion 211b may be formed in a cylindrical shape having both ends open. One end of the cylindrical portion 211b can be fitted through the opening of the pressing member 211a. The outer periphery of the cylindrical portion 211b may be screwed to the pressing member 211a, but is not limited thereto. A ring member 211ba may be formed on the inner peripheral surface of the cylindrical portion 211b. The ring member 211ba is formed to have a predetermined diameter. The ring member 211ba is formed such that its inner peripheral surface is in contact with the outer peripheral surface of the hollow tube portion 213. [

The hollow tube portion 213 may be a tubular shape having openings at both ends thereof. The hollow tube portion 213 may be configured to have a first inner space sp1 and a second inner space sp2 that is bulkier than the first inner space sp1. The hollow tube portion 213 may have a left portion constituting the second inner space sp2 inside the cylindrical portion 211b. The hollow tube portion 213 can be fixed to the vane expanding portion 220 with a right portion constituting the first inner space sp1. The hollow tube portion 213 may have a protruding ring portion 213a formed on the outer circumference of the central portion. The protruding ring portion 213a may be provided such that one end of the protruding ring portion 213a abuts against the vane expanding portion 220.

On the other hand, a separation signal line (wire1) can be connected to the protruding ring portion 213a. The separation signal line wire1 is electrically connected to the sensing signal line wire2. When the separation mechanism 210 is separated from the vane expanding part 220, the separation signal line wire1 is disconnected from the sensing signal line wire2. When the electrical connection between the separation signal line (wire1) and the sensing signal line (wire2) is released, separation of the separation mechanism 210 and the blade expansion unit 220 is sensed by a sensing device (not shown) That is, the separation of the parachute structure 300 can be sensed by disconnecting the separation signal line wire1 and the sensing signal line wire2.

The hollow tube portion 213 may be formed with a support portion 213b on the outer circumference of the left portion constituting the second inner space sp2. The support portion 213b may have an outer diameter to be in contact with the inner circumferential surface of the cylindrical portion 211b.

The first spring S1 may be provided between the support portion 213b of the hollow tube portion 213 and the ring member 211ba of the cylindrical portion 211b. The first spring S1 is provided to surround the left portion of the hollow tube portion 213. [ The first spring S1 has an elastic restoring force for pushing the cylindrical portion 211b to the right.

A gap holding portion 130 may be provided between the protruding ring portion 213a of the hollow tube portion 213 and the ring member 211ba of the cylindrical portion 211b. At least two spacing members 130 may be provided on the upper and lower portions of the hollow tube 213. The gap holding portion 130 has a proper length so that the protruding ring portion 213a of the hollow tube portion 213 and the ring member 211ba of the cylindrical portion 211b are spaced apart from each other by a predetermined distance.

A fixing pin portion 215 is provided inside the hollow tube portion 213. The fixing pin portion 215 has a length such that one end is located inside the cylindrical portion 211b and the other end is located at the right side portion of the hollow tube portion 213. [ A fixing member (fx) provided through the outer periphery of the hollow tube portion (213) is closely attached to the outer periphery of the fixing pin portion (215). The fixing pin portion 215 can fix the hollow tube portion 213 to the receiving portion 221 by pressing the fixing member fx so as to be positioned in the through hole h of the receiving portion 221. [

The fixed pin portion 215 may be formed with a receiving groove 215a at a predetermined outer circumferential portion. The receiving groove 215a can receive the holding member fx when positioned so as to face the holding member fx. When the fixing member fx is received in the receiving groove 215a, the hollow tube portion 213 is released from the receiving portion 221 and the separating mechanism 210 is separated from the blade expanding portion 220. [

The holding pin portion 215 may be formed with a receiving portion 215b at a predetermined outer circumferential portion located in the second inner space sp2 of the hollow tube portion 213. [ The receiving portion 215b may have an outer diameter to abut the inner circumferential surface of the left portion of the hollow tube portion 213 forming the second inner space sp2.

A second spring S2 is provided in the second inner space sp2 of the hollow tube 213 to surround the fixing pin 215. The second spring S2 is provided such that its one end abuts against the receiving portion 215b and the other end abuts against the inner vertical surface of the hollow tube portion 213 forming the second inner space sp2. And the second spring S2 is provided in an uncompressed state. When the second spring S2 is compressed by the pressing member 211a, the second spring S2 has an elastic restoring force for pushing the fixing pin portion to the left. The operation of the second spring S2 can be confirmed through FIG. 6, which will be described later.

The stopper 217 is coupled to the left end of the hollow tube 213. The fixing stopper 217 is formed with a through hole at the center so that the fixing pin portion 215 is penetrated. The stationary stopper 217 is provided so as to abut against the receiving portion 215b of the stationary pin portion 215 as usual. The fixing cap 217 supports the fixing pin portion 215 so as not to escape out of the hollow tube portion 213.

The blade expansion unit 220 is detachably connected to the separation mechanism 210. The wing expansion part 220 is connected to the front wing 400 and the rear wing 500, respectively. The vane deployment portion 220 may deploy the front vane 400 and the rear vane 500 simultaneously according to the resistance of the parachute structure 300. The blade expanding unit 220 can separate the separation mechanism 210 when the development of the front blade 400 and the rear blade 500 is completed. To this end, the vane deployment portion 220 may include a receiving portion 221, a rod portion 223, and a vertical axis portion 225.

The receiving portion 221 may be formed in a cylindrical shape. The receiving portion 221 may be formed so that one end thereof is opened and has an opening. The receiving portion 221 can receive the separating mechanism 210 through the opening at one end. In particular, the receiving portion 221 can receive the hollow tube portion 213 and the fixing pin portion 215. When the hollow tube portion 213 and the fixing pin portion 215 are received in the receiving portion 221, the projecting ring portion 213a of the hollow tube portion 213 is closely contacted with one end of the receiving portion 221. The sensing signal line (wire2) described above is connected to the other end of the accommodating portion 221. [

The receiving portion 221 may have a through hole h formed at a predetermined outer circumferential portion thereof. At least a part of the fixing member fx may be positioned in the through hole h of the accommodating portion 221. [ It is preferable that the through hole h of the accommodating portion 221 is formed to have a smaller diameter than the outer diameter of the fixing member fx. At least a part of the fixing member fx is located in the through hole h and penetrates the hollow tube portion 113 and is brought into close contact with the fixing pin portion 115 so that the hollow tube portion 113 is fixed inside the accommodating portion 221 .

One end of the rod portion 223 is connected to the other end of the receiving portion 221. The other end of the rod portion 223 is connected to the front blade 400. The rod portion 223 can pull the front blades 400 as the receiving portion 221 moves to the left. The rod portion 223 can be opened by rotating the front blades 400 through the pulling action.

The vertical shaft portion 225 is formed on the outer periphery of the receiving portion 221. The vertical shaft portion 225 is formed to extend downward from the outer periphery of the receiving portion 221. The vertical axis portion 225 may have a circular rod shape, but is not limited thereto. A rear pulling rod 250, which is used to pivot the rear wing 500, may be connected to the vertical axis portion 225.

3, the rear rotary shaft portion 240 is provided for rotating the rear blades 500 and includes a rear rotary shaft 241, a rotary shaft fixing portion 243, and a plurality of bearings 245, 247, and 249 .

The rear rotation shaft 241 may have a cylindrical shape. A rear blade (500) is rotatably connected to the rear rotation shaft (241). The rotation axis fixing portion 243 is provided on the same axis as the rear rotation axis 241. The rotation axis fixing portion 243 is coupled to the rear of the flying body 100 (see FIG. 2). The plurality of bearings 245, 247, and 249 are provided to surround the rear rotation shaft 241. The plurality of bearings 245, 247, and 249 are stacked with the rear blades 500 interposed therebetween.

The plurality of bearings includes first, second, and third bearings 245, 247, 249. The first, second and third bearings 245, 247 and 249 are preferably thrust bearings. For example, the first bearing 245 is provided to surround the lower portion of the rear rotation shaft 241. A left rear blade 510 is stacked on the first bearing 245. The second bearing 247 is provided on the upper portion of the left rear blade 510 while enclosing the rear rotation shaft 241. The right rear blades 520 are stacked on the second bearing 247. The third bearing 249 is provided on the right rear blade 520 while enclosing the rear rotation shaft 241.

The rear pulling rod 250 includes first and second rear pulling rods 251, 253. The first rear pulling rod 251 connects the left rear blade 510 and the rear rotation shaft 241. One end of the first rear pulling rod 251 is fixed to the left rear blade 510 by a fixing pin pin1. The other end of the first rear pulling rod 251 is rotatably connected to the vertical axis portion 225 of the vane expanding portion 220.

The second rear pulling rod 253 connects the right rear blade 520 and the rear rotation shaft 241. The second rear pulling rod 253 is fixed to the right rear blade 520 at one end by a fixing pin pin2. The other end of the second rear pulling rod 253 is rotatably connected to the vertical axis portion 225 of the vane expanding portion 220.

The front rotary shaft portion 260 and the front pulling rod 270 are used for rotating and expanding the front blades 400 and will be described later with reference to FIGS.

5 and 6, the blade expanding process by the blade expanding unit 220 of the blade expander 200 and the separation process of the separation mechanism 210 will be described in detail.

In Figure 5, when the flight body 100 is released into the air, the parachute structure 300 is unfolded and resistive, and the resilient force of the parachute structure 300 causes tension on the connecting strap 310 of the parachute structure 300 . The connection portion 211 is pulled to the left side (reference in FIG. 5) by the tension of the connection cord 310. At this time, the first spring S1 is compressed by the cylindrical portion 211b of the connection portion 211. Here, it is preferable that the first spring S1 is compressed when sufficient resistance is generated in the parachute structure 300.

The gap between the ring member 211ba of the cylindrical portion 211b and the projecting ring portion 213a of the hollow tube portion 213 is spaced apart. At this time, one end of each of the first gap retaining portion 231 and the second gap retaining portion 233 is not in contact with the ring member 211ba of the cylindrical portion 211b and is completely removed from the outside of the cylindrical portion 211b . Since the first gap retaining portion 231 and the second gap retaining portion 233 are provided with the leaf springs vs1 and vs2, the vertical spacing of the leaf springs vs1, vs2 at the moment of deviation from the outside of the cylindrical portion 211b, And is separated from the lower and upper portions of the hollow tube portion 213 by the directional elastic force.

In addition, since the hollow tube portion 213 of the separation mechanism 210 is fixed, the vane expanding portion 220 can be separated by the tension of the connection cord 310, which is continued after the first spring S1 is completely compressed, (210). At this time, the vane expanding unit 220 opens the front vane 400 by pulling the front pulling rod 270 through the rod unit 223. In addition, the blade expanding unit 220 develops the rear blades 510 and 520 by pulling the rear pulling rods 251 and 253 through the vertical axis unit 225. Here, the opening operation of the front blades 400 and the rear blades 500 by the blade expanding unit 220 can be confirmed through FIGS. 8A and 8B.

6, after the flight body 100 has been sufficiently decelerated by the parachute structure 300, the resistance of the parachute structure 300 is weak enough to not compress the first spring S1, that is, the parachute structure 300 Is proportional to the square of the speed of the flight main body 100, so that if the flight main body 100 is decelerated below a certain speed, it does not have the force to compress the first spring S1.

At this time, the first spring S1 expands through elastic restoring force, thereby pushing the cylindrical portion 211b to the right. Here, the interval between the ring member 211ba of the cylindrical portion 211b and the protruding ring portion 213a of the hollow tube portion 213 becomes narrow.

Since the pressing member 211a is coupled to the cylindrical portion 211b, the pressing member 211a moves to the right along with the cylindrical portion 211b. The pressing member 211a comes into contact with the left end of the fixing pin portion 215 while moving to the right side and presses the fixing pin portion 215 continuously to move it to the right side. At this time, the receiving portion 215b of the fixing pin portion 215 is separated from the fixing stopper 217 to compress the second spring S2. Here, in order for the second spring S2 to be compressed, it is preferable that the first spring S1 has greater elastic restoring force than the second spring S2.

The right end of the fixing pin portion 215 is deeply inserted into the receiving portion 221 of the vane expanding portion 220 and the receiving groove 215a of the fixing pin portion 215 is inserted into the fixing portion fx and the receiving portion 221 Through the through hole (h). At this time, a predetermined portion of the fixing member fx, which is located in the through hole h of the receiving portion 221, comes out and a predetermined portion of the fixing member fx is located in the receiving groove 215a. The hollow tube portion 213 is released from the receiving portion 221 and completely escaped to the outside of the receiving portion 221 by the resisting force remaining in the parachute structure 300 and the elastic restoring force of the second spring S2 . That is, the separating mechanism 210 is disconnected from the vane expanding part 220, and the separated signal line wire1 is disconnected and the sensing signal line wire2 is electrically opened. The sensing device provided in the flying body 100 detects that the separating mechanism 210 is separated through the sensing signal wire wire2 and operates the power unit to drive the propeller unit 600. [

Referring to FIGS. 7 and 8, the development process of the front blades 400 and the rear blades 500 by the blade expansion device 200 according to the embodiment of the present invention can be confirmed.

7 (a) is a view showing the front blades 400 before being developed, and FIG. 7 (b) is a view showing the rear blades 500 before being developed. 8 (a) is a view showing a front wing 400 in a deployed state, and FIG. 8 (b) is a view showing a rear wing 500 in a deployed state.

7A, the left front blades 410 and the right front blades 420 are overlapped and positioned at the upper portion of the flying body 100. As shown in Fig. Here, the left front blades 410 and the right front blades 420 are rotatably connected to the front rotation shaft 260. The left front wing 410 is connected to the rod portion 223 of the vane deploying portion 220 by a first front pulling rod 271. The right front blade 420 is connected to the rod portion 223 of the blade expanding portion 220 by a second front pulling rod 273.

In FIG. 7 (b), the left rear blade 510 and the right rear blade 520 overlap and are positioned at the bottom of the flying body 100. Here, the left rear blade 510 and the right rear blade 520 are rotatably connected to the rear rotation shaft 241. The left rear blade 510 is connected to the vertical axis portion 225 (see FIG. 3) of the vane deployment portion 220 by a first rear pulling rod 251. The right rear blade 520 is connected to the vertical axis portion 225 (see FIG. 3) of the vane deployment portion 220 by a second rear pulling rod 253.

8 (a), when the rod portion 223 is pulled together with the separation mechanism 210 by the resistance of the parachute structure 300, the left front blade 410 rotates clockwise about the front rotation shaft 260 And the right front blades 420 rotate counterclockwise about the front rotation shaft 260 and are arranged vertically to the right side of the flying body 100 . At this time, the left front wing 410 and the right front wing 420 can provide a lift force for flight of the flight body 100 in front of the flight body 100.

8 (b), when the rod portion 223 is pulled together with the separation mechanism 210 by the resistance of the parachute structure 300, the left rear blade 510 rotates about the rear rotation axis 241 The right rear blade 520 is rotated clockwise around the rear rotation shaft 241 and is disposed perpendicular to the right side of the flying body 100 . At this time, the left rear wing 510 and the right rear wing 520 may provide a lift force for the flight of the flight body 100 to the rear of the flight body 100.

It will be apparent to those skilled in the art that various modifications, substitutions and substitutions are possible, without departing from the scope and spirit of the invention as disclosed in the accompanying claims. will be. Therefore, the embodiments disclosed in the present invention and the accompanying drawings are intended to illustrate and not to limit the technical spirit of the present invention, and the scope of the technical idea of the present invention is not limited by these embodiments and the accompanying drawings .

10: Aircraft
100: Flight body
200: blade expansion device
210: separating mechanism
211: Connection
211a: pressing member
211b:
211ba: ring member
213: hollow tube portion
sp1, sp2: first and second inner spaces
213a: protruding ring portion
213b:
S1, S2: First and second springs
215:
215a: receiving groove
215b:
220:
221:
h: Through hole
fx: Fixing member
223:
225:
230:
240: rear rotating shaft portion
241:
243:
245, 147, 149: first, second and third bearings
250: rear pulling rod
251, 153: first and second rear pulling rods
260: front rotary shaft
270: front pulling rod
271, 273: first and second front pulling rods
300: Parachute structure
310: connection cord
400: front wing
410: left front wing
420: right front wing
500: rear wing
510: left rear wing
520: right rear wing
600: Propeller section
610: Frame structure
620: drive shaft
630: Propeller body
640: Wings
700: search device

Claims (14)

A separation mechanism to which the parachute structure is connected; And
A vane deployment unit detachably connected to the separation mechanism and connected to each of a front wing and a rear wing of a flying body and deploying the front wing and the rear wing according to resistance of the parachute structure;
Lt; / RTI >
The vane expanding portion includes a receiving portion having one end opened and having an opening and receiving the separating mechanism through the opening, a rod portion having one end connected to the other end of the receiving portion and the other end connected to the front wing, And a vertical axis portion formed on the upper surface of the housing,
The rear wing is connected to the vertical shaft portion by a rear pulling rod,
Wherein the receiving portion is formed with a through hole such that at least a part of the holding member for fixing the separating mechanism to the inside of the receiving portion is located,
Wherein the separating mechanism includes a connecting portion to which the parachute structure is connected, a hollow tube portion to be coupled with the connecting portion, and a fixing pin portion provided inside the hollow tube portion,
Wherein the hollow tube portion is fixed to the inside of the accommodating portion by being pierced by the fixing member and at least a part of the fixing member is located in the through hole while the fixing member is in close contact with the fixing pin portion. . delete delete delete The method according to claim 1,
The connecting portion
And a cylindrical portion which is formed to surround the hollow tube portion and the fixing pin portion and is open at both ends, the cylindrical portion being connected to the pressing member,
Wherein the cylindrical portion has a ring member formed on an inner circumferential surface thereof. 6. The method of claim 5,
Wherein the hollow tube portion has a protruding ring portion formed on the outer periphery of the center portion,
And a gap holding portion is provided between the protruding ring portion and the ring member. 6. The method of claim 5,
Wherein the hollow tube portion has a support portion formed on an outer periphery of one end thereof,
And a first spring is provided between the support portion and the ring member. 8. The method of claim 7,
Wherein the hollow tube portion is configured to have a first inner space and a second inner space having a larger volume than the first inner space,
Wherein the second inner space is provided with a second spring to surround the fixing pin portion. 9. The method of claim 8,
Wherein the first spring has an elastic restoring force greater than that of the second spring. 9. The method of claim 8,
Wherein the fixing pin portion has a receiving groove formed on an outer circumference thereof,
Wherein the hollow tube portion is released from the receiving portion when the holding member is received in the receiving groove. The method according to claim 1,
A rear rotation shaft to which the rear wing is rotatably connected, a rotation shaft fixing unit provided on the same axis as the rear rotation shaft, and a plurality of bearings disposed to be laminated with the rear wing interposed therebetween And a rear rotating shaft portion for rotating the blade. The method according to claim 1,
Further comprising a front rotary shaft to which the front blades are rotatably connected,
And the front wing is connected to the rod by a front pulling rod. Flight body;
The vane deployment device according to any one of claims 1 and 5 to 12, provided in the flying body.
A parachute structure connected to the vane deployment device;
A front blade rotatably connected to the front of the flying body;
A rear blade rotatably connected to the rear of the flying body; And
A propeller provided at the rear of the flying body to provide a driving force to the flying body;
And a vane deployment device including the vane deployment device. 14. The method of claim 13,
The propeller unit,
A propeller body rotatably connected to the drive shaft, and a rotatable shaft rotatably connected to both ends of the propeller body, wherein the propeller body includes: a frame structure provided in the flying body; a drive shaft passing through the frame structure and connected to a power unit of the flying body; And a pair of wings.

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