KR101901892B1 - Driving device for wing of guided aircraft - Google Patents

Driving device for wing of guided aircraft Download PDF

Info

Publication number
KR101901892B1
KR101901892B1 KR1020180000766A KR20180000766A KR101901892B1 KR 101901892 B1 KR101901892 B1 KR 101901892B1 KR 1020180000766 A KR1020180000766 A KR 1020180000766A KR 20180000766 A KR20180000766 A KR 20180000766A KR 101901892 B1 KR101901892 B1 KR 101901892B1
Authority
KR
South Korea
Prior art keywords
wing
drive shaft
support member
spreading
unfolding
Prior art date
Application number
KR1020180000766A
Other languages
Korean (ko)
Inventor
윤무관
심영호
이상은
김형철
한성재
박승운
최용준
Original Assignee
(주)경인테크
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by (주)경인테크 filed Critical (주)경인테크
Application granted granted Critical
Publication of KR101901892B1 publication Critical patent/KR101901892B1/en

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/62—Steering by movement of flight surfaces
    • F42B10/64—Steering by movement of flight surfaces of fins

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Abstract

The present invention relates to a wing driving device of a guided flight vehicle, comprising: a support member; a wind driving shaft and a wing driving unit installed on the support member to be able to rotate; a wing rotating and supporting member installed to be able to rotate on the wing driving shaft; a wing member to rotate between an unfolded state extended along an axial line of the wing driving shaft and a folded state bent from the axial line; and an unfolding engagement unit disposed in the wing driving shaft and the wing member. The unfolding engagement unit includes an unfolding stopping groove disposed in any one of the wing driving shaft and the wing member, and an unfolding stopping protrusion disposed in another one. As the unfolding stopping protrusion is inserted into the unfolding stopping groove by rotation of the wing driving shaft, the wing member is switched over to the unfolded state and the rotational amount of the wing member is adjusted in accordance with the rotation of the wing driving shaft. Accordingly, the unfolded and folded states of the wing member can be stably maintained with a simple structure due to the unfolding engagement unit.

Description

유도비행체의 날개구동장치{DRIVING DEVICE FOR WING OF GUIDED AIRCRAFT}BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to a driving device,

본 발명은 유도비행체의 날개구동장치에 관한 것이다.BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an apparatus for driving a wing of an induction vehicle.

미사일과 같은 유도비행체는 발사대로부터 발사되어 상승하며, 최고점에 이르면 중력에 의해 지상으로 하강한다. 이러한 유도비행체에 접이식 날개를 장착하면, 최고점에서 하강할 때 날개가 전개되어 유도비행체의 정확한 비행을 유도하고 사거리를 연장할 수 있어 정밀한 타격이 가능해진다.A guided vehicle, such as a missile, is fired from the launcher and ascends to the ground by gravity when it reaches its peak. When a folding wing is mounted on such an induction vehicle, the wing is deployed when descending from the peak, which can induce accurate flight of the guided vehicle and extend the range, thereby enabling precise hitting.

이를 위해, 종래의 접이식 날개는 날개가 유도비행체 내부에 접힌 상태에서 발사되어 필요 시 날개가 전개되도록 설치되는데, 날개가 접혀진 상태와 펼쳐진 상태를 유지하기 위한 구조가 복잡하였고, 충격에 의해 날개가 원하지 않는 위치에서 펼쳐지거나, 펼쳐진 후 펼침상태를 안정적으로 유지하지 못하는 문제점이 있었다.To this end, the conventional folding wing is installed such that the wing is fired in a folded state inside the guide flight body, and the wing is deployed when necessary. The structure for holding the folded wing and the unfolded state is complicated. There is a problem in that it can not be stably maintained in the unfolded state after being unfolded or unfolded in a non-unfolded position.

본 발명은 날개의 접힘상태와 펼침상태가 안정적으로 유지되는 간단한 구조의 유도비행체의 날개구동장치를 제공하는 것이다.The present invention provides an apparatus for driving a wing of an induction vehicle having a simple structure in which the folded state and the unfolded state of the wing are stably maintained.

상기 목적은, 본 발명에 따라, 유도비행체의 날개구동장치에 있어서, 상기 유도비행체에 설치되며 날개멈춤부를 갖는 지지부재와, 상기 지지부재에 회전가능하게 설치되는 날개구동축과, 상기 날개구동축을 회전구동하는 날개구동부와, 상기 날개구동축에 대해 상대회동가능하게 설치되는 날개회동지지부재와, 상기 날개구동축의 축선을 따라 연장된 펼침상태와, 상기 축선에 대해 절곡된 접힘상태 간을 회동 가능하도록 상기 날개회동지지부재에 힌지 결합되며 접힘상태에서 날개멈춤부에 의해 상기 날개구동축의 회전방향에 따른 회동이 저지되는 날개부재와, 상기 날개부재를 상기 날개회동지지부재에 대하여 펼침상태 방향으로 탄성적으로 미는 탄성부재와, 상기 날개구동축과 상기 날개부재 중 어느 하나에 마련된 펼침멈춤홈과 다른 하나에 마련되어 상기 펼침멈춤홈에 상호 맞물리도록 마련된 펼침멈춤돌기를 가지며, 상기 날개구동축의 소정의 회전위치에서 상기 펼침멈춤홈과 상기 펼침멈춤돌기가 상호 맞물리며 상기 날개부재가 접힘상태에서 펼침상태로 전환하게 하는 펼침물림부를 포함하는 것을 특징으로 하는 유도비행체의 날개구동장치에 의해 달성된다.According to the present invention, there is provided an apparatus for driving a wing drive of an induction vehicle, comprising: a support member provided on the guide body and having a wing stop; a wing drive shaft rotatably installed on the support member; A wing drive unit for driving the wing drive shaft, a wing pivot support member installed to be rotatable relative to the wing drive shaft, a wedge drive unit for rotating the wing drive shaft in a unfolded state extending along an axis of the wing drive shaft, A wing member hinged to a wing pivotal support member and being prevented from rotating in a folded state by a wing stop in accordance with a rotation direction of the wing drive shaft, and a wing member elastically biasing the wing member toward the wing pivot support member Wherein the pushing elastic member and the deploying stop groove provided on any one of the wing drive shaft and the wing member and And the spreading stop groove and the spreading stop protrusion are engaged with each other at a predetermined rotational position of the wing drive shaft so that the wing member is switched from the folded state to the extended state And a wedge drive device for guiding the wing.

여기서, 상기 날개부재의 펼침상태와 접힘상태에 따른 상기 날개구동축의 회전저항과 상기 날개부재가 상기 날개구동축과 일체회전할 때의 회전량을 감지하는 회전량감지부를 가지는 것이 바람직하다.It is preferable to have a rotation amount sensing unit that senses a rotation resistance of the wing drive shaft according to the unfolded state and the folded state of the wing member and a rotation amount when the wing member rotates integrally with the wing drive shaft.

그리고, 상기 날개부재가 펼침상태를 유지하도록 상기 날개회동지지부재와 상기 날개부재 중 어느 하나에 마련된 고정홈과 다른 하나에 마련되어 상기 고정홈에 상호 맞물리는 고정핀을 가지는 펼침유지부를 더 포함하는 것으로 날개부재의 펼침상태를 안정적으로 유지할 수 있다.Further, the present invention may further include a deployed holding unit having a fixed pin provided on the other of the fixed grooves provided in any one of the wing pivotal support member and the wing member so as to maintain the wing member in the unfolded state, The spreading state of the wing members can be stably maintained.

또한, 상기 펼침멈춤돌기는 상기 펼침멈춤홈에 삽입되는 선단영역이 타 영역에 비해 좁게 형성되어 펼침멈춤돌기가 펼침물림홈에 용이하게 삽입될 수 있다.In addition, the spreading protrusion may be formed to be narrower than the other regions, so that the spreading stop protrusion can be easily inserted into the spreading groove.

그리고, 상기 날개구동부는 상기 날개구동축과 일체회전하는 웜휠과 상기 웜휠과 맞물리는 웜기어 및 상기 웜기어를 회전시키는 구동모터를 포함하는 것이 바람직하다.The wing driving unit may include a worm wheel that rotates integrally with the wing drive shaft, a worm gear that engages with the worm wheel, and a driving motor that rotates the worm gear.

본 발명에 따른 유도비행체의 날개구동장치는 날개의 접힘상태와 펼침상태가 안정적으로 유지되며, 간단한 구조를 가진다.The wing drive device according to the present invention has a simple structure in which the folded state and the unfolded state of the wing are stably maintained.

도 1은 본 발명에 따른 유도비행체의 날개구동장치의 사시도이고,
도 2는 본 발명에 따른 유도비행체의 날개구동장치의 단면도이고,
도 3은 본 발명에 따른 유도비행체의 날개구동장치의 분해사시도이고,
도 4는 날개부재가 접힘상태를 나타내는 사시도이고,
도 5는 날개부재가 펼쳐지려는 상태를 나타내는 사시도이고,
도 6은 날개부재가 펼쳐지려는 상태에서의 단면도이고,
도 7은 펼침유지부를 나타내는 부분단면도이고,
도 8은 일체회동유지부를 나타내는 부분단면도이다.1 is a perspective view of an apparatus for driving a wing of an induction vehicle according to the present invention,
FIG. 2 is a cross-sectional view of a wing drive device of an induction vehicle according to the present invention,
3 is an exploded perspective view of a wing drive device of an induction vehicle according to the present invention,
4 is a perspective view showing a folded state of a wing member,
5 is a perspective view showing a state in which a wing member is to be unfolded,
6 is a cross-sectional view in a state in which the wing member is to be unfolded,
7 is a partial sectional view showing the unfolding holding portion,
8 is a partial cross-sectional view showing the integral rotation holding portion.

이하 본 발명에 따른 유도비행체의 날개구동장치를 첨부된 도면을 참조하여 상세히 설명한다.DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, an apparatus for driving a wing of an induction vehicle according to the present invention will be described in detail with reference to the accompanying drawings.

도 1 내지 도 8에 도시된 바와 같이, 본 발명에 따른 유도비행체의 날개구동장치는 지지부재(100)와, 날개구동축(200) 및 날개구동축(200)을 회전시키는 날개구동부와, 날개회동지지부재(300)와. 날개부재(400)를 가진다.1 to 8, an apparatus for driving a wing of an induction vehicle according to the present invention includes a supporting member 100, a wing driving unit for rotating the wing driving shaft 200 and the wing driving shaft 200, Member 300 and. And has a wing member (400).

본 발명에 따른 유도비행체는 포탄과 같이 지상 또는 공중에서 발사되어 일정 위치까지 도달한 후 날개부재(400)가 펼쳐져 활공시간을 늘려 정확한 목표물까지 이동될 수 있도록 한다. 지지부재(100)는 이러한 유도비행체에 설치되며, 날개부재(400)의 개수와 동일하게 설치된다. 지지부재(100)는 날개부재(400)의 전개방향에 따라서 유도비행체의 전방 또는 후방에 설치 가능하다.The guided vehicle according to the present invention is launched from the ground or air such as a shell and reaches a predetermined position, and then the wing member 400 is unfolded so that the glide time can be extended to the correct target. The support member 100 is installed on the guide body and is installed in the same number as the wing members 400. The support member 100 can be installed in front of or behind the guide body along the direction in which the wing members 400 are deployed.

지지부재(100)는 날개부재(400)가 접힘상태로 설치될 때 날개부재(400)의 최초위치를 고정하기 위한 날개멈춤부(110)가 형성되어 있다. 날개멈춤부(110)는 날개부재(400)가 접혀져서 삽입되었을 때 날개부재(400)가 펼쳐지는 평면의 수직한 방향으로 날개부재(400)가 이동하는 것을 차단한다.The support member 100 has a wing stopper 110 for fixing the initial position of the wing member 400 when the wing member 400 is installed in a folded state. The wing stopper 110 blocks the wing member 400 from moving in a direction perpendicular to the plane on which the wing member 400 is extended when the wing member 400 is folded and inserted.

지지부재(100)는 지지부재(100)에 회전가능하게 설치되는 날개구동축(200)을 가진다. 날개구동축(200)은 축선의 방향이 유도비행체의 길이방향에 수직한 방향을 가지며, 유도비행체의 외측방향의 원형 끝 단면인 가동면의 중심에서 내부로 길이방향을 따라 길게 절취되어 형성된 원형삽입홈(202)을 가진다. 이러한 날개구동축(200)에는 날개구동축(200)을 회전구동하는 날개구동부가 결합된다.The support member 100 has a wing drive shaft 200 rotatably installed on the support member 100. The wing drive shaft 200 has a circular insertion groove formed in a longitudinal direction of the wing drive shaft 200 and having a direction perpendicular to the longitudinal direction of the guide flight body and being cut from the center of the movable face, (202). The wing driving shaft 200 is coupled with a wing driving unit for driving the wing driving shaft 200 to rotate.

지지부재(100)에는 날개구동축(200)과 동일한 축선을 가지며 날개구동축(200)의 원형삽입홈(202)에 삽입되는 결합축(302)을 가지고, 날개구동축(200)에 대해 상대회동가능하게 설치되는 날개회동지지부재(300)가 설치된다. The supporting member 100 has an engaging shaft 302 having the same axis as that of the wing driving shaft 200 and inserted into the circular insertion groove 202 of the wing driving shaft 200 and is rotatable relative to the wing driving shaft 200 And a wing pivotal support member 300 is installed.

날개회동지지부재(300)는 날개부재(400)가 삽입되기 위한 날개부재삽입홈(310)이 형성되며, 날개부재삽입홈(310)은 날개부재(400)가 접힘상태와 펼침상태의 전환 시 날개부재(400)의 간섭이 없도록 하는 개방부(311)와, 날개부재(400)가 펼치지는 평면의 가로방향으로의 이동을 저지하는 날개지지면을 가진다. 날개회동지지부재(300)는 후술하게 될 펼침물림부를 통해 날개부재(400)가 접혀진 상태에서는 날개구동축(200)과 독립적으로 회동되고, 날개부재(400)가 펼쳐진 상태에서는 날개구동축(200)과 일체회전하게 된다.The wing pivot support member 300 is formed with a wing member insertion groove 310 for inserting the wing member 400 and the wing member insertion groove 310 is formed in a state where the wing member 400 is in the collapsed state and in the switching state An opening 311 for preventing the wing member 400 from interfering with the wing member 400 and a wing support surface for preventing movement of the plane in which the wing member 400 is extended in the lateral direction. The wing pivot support member 300 rotates independently of the wing drive shaft 200 in a state in which the wing member 400 is folded through the unfolding portion to be described later and when the wing member 400 is unfolded, So that it rotates integrally.

날개회동지지부재(300)의 날개부재삽입홈(310)에는 날개구동축(200)의 축선을 따라 연장된 펼침상태와, 축선에 대해 절곡된 접힘상태 간을 회동가능하도록 날개회동지지부재(300)에 힌지 결합되며 접힘상태에서 날개멈춤부(110)에 의해 날개구동축(200)의 회전방향에 따른 회동이 저지되는 날개부재(400)가 설치된다.The wing pivot support member 300 is rotatably supported by the wing member insertion groove 310 of the wing pivot support member 300 so as to be rotatable between an extended state extending along the axis of the wing drive shaft 200 and a folded state bent toward the axis, And a wing member 400 which is hinged to the wing stopper 110 and is prevented from rotating in the direction of rotation of the wing drive shaft 200 by the wing stopper 110 in a folded state.

날개부재(400)는 펼침상태에서 공기의 저항을 받을 수 있도록 판면을 가지는 날개본체(410)와 날개본체(410)의 일단에서 연장되어 날개회동지지부재(300)와 힌지 결합되는 날개전개축(420)을 가진다.The wing member 400 includes a wing body 410 having a plate surface to receive resistance of air in an unfolded state and a wing deployment axis extending from one end of the wing body 410 and hinged to the wing pivot support member 300 420).

날개전개축(420)은 폭방향을 관통하여 형성되는 회동홈(425)을 가지며, 회동홈(425)에는 날개회동지지부재(300)의 날개지지면에 설치되는 회동핀(313)이 삽입된다. 이에 따라 회동핀(313)의 일단과 날개전개축(420)은 도 6에 도시된 바와 같이 결합핀(426)에 의해 상호 결합되어 일체 회전하며, 회동핀(313)의 타단에는 도 4. 5. 8에 도시된 바와 같이 축선방향을 따라 내측으로 절취된 비틀림스프링고정홈(313A)이 형성된다. The blade expansion shaft 420 has a rotation groove 425 formed through the width direction and a rotation pin 313 provided on the blade support surface of the blade rotation support member 300 is inserted into the rotation groove 425 . As a result, one end of the pivot pin 313 and the pivot deployment axis 420 are coupled to each other by the engagement pin 426 as shown in Fig. 6, A torsion spring fixing groove 313A cut inward along the axial direction is formed as shown in Fig.

날개회동지지부재(300)에는 날개부재(400)를 날개회동지지부재(300)에 대하여 펼침상태 방향으로 탄성적으로 미는 탄성부재가 설치된다. 본 발명에서의 탄성부재는 비틀림스프링(321)으로 형성되어 있지만, 이는 날개부재(400)를 탄성적으로 밀기위한 다양한 방법 중에서 선택가능한 정도이다.The wing pivot support member 300 is provided with an elastic member that resiliently urges the wing member 400 in the unfolding direction with respect to the wing pivot support member 300. Although the elastic member in the present invention is formed by the torsion spring 321, it is selectable from among various methods for elastically pushing the wing member 400.

날개회동지지부재(300)는 지지면의 일부영역에 비틀림스프링(321)을 수용하여 그 일단을 지지하는 스프링삽입홈(312)을 갖는다. 비틀림스프링(321)은 그 일단이 스프링삽임홈(312)에 삽입되어 있고 그 타단이 가령 비틀림스프링고정홈(313A)에 삽입되어 있으므로 날개부재(400)의 펼침상태에서 비틀림에 의한 탄성을 유지할 수 있도록 설치된다. 이러한 비틀림스프링(321)은 날개부재(400)가 접힘상태로 접혀질 때 날개부재(400)를 펼침상태 방향으로 탄성력을 가하게 된다.The blade pivot support member 300 has a spring insertion groove 312 for receiving a torsion spring 321 and supporting one end of the torsion spring 321 in a part of the support surface. Since the torsion spring 321 has one end inserted into the spring insertion groove 312 and the other end inserted into the torsion spring fixing groove 313A, the torsion spring 321 can maintain the elasticity due to the torsion in the extended state of the wing member 400 . The torsion spring 321 applies an elastic force to the wing member 400 in the unfolding direction when the wing member 400 is folded in a folded state.

본 발명은 날개구동축(200)과 날개전개축(420) 중 어느 하나에 마련된 펼침멈춤홈(210)과 다른 하나에 마련되어 펼침멈춤홈(210)에 상호 맞물리도록 마련된 펼침멈춤돌기(421)를 가지며, 날개구동축(200)의 소정의 회전위치에서 펼침멈춤홈(210)과 펼침멈춤돌기(421)가 상호 맞물리며 날개부재(400)가 접힘상태에서 펼침상태로 전환하게 하는 펼침물림부를 가진다.The present invention has a spreading stopper 421 provided on one of the spreading stopper grooves 210 provided on one of the wing drive shaft 200 and the blade expanding shaft 420 and adapted to be engaged with the spreading stopper groove 210 And the unfolding stop groove 210 and the unfolding stopper 421 are engaged with each other at a predetermined rotation position of the wing drive shaft 200 to allow the wing member 400 to change from the folded state to the unfolded state.

본 발명에서는 펼침멈춤돌기(421)가 날개부재(400)의 날개전개축(420)에 형성되고, 펼침멈춤홈(210)은 날개구동축(200)에 형성된다. 이로 인해 펼침물림부를 형성하기 위한 제조원가가 절감되는 효과가 있으나, 이와 반대로 형성할 수도 있다.In the present invention, the spreading stopper 421 is formed on the blade spreading shaft 420 of the wing member 400, and the spreading stopper groove 210 is formed on the blade drive shaft 200. This has the effect of reducing the manufacturing cost to form the spreading part, but it can also be formed in the opposite manner.

펼침멈춤홈(210)은 날개구동축(200)의 축 끝단 즉, 유도비행체의 원주방향을 향하는 방향에 위치한 날개구동축(200)의 가동면에 형성된다. 펼침멈춤홈(210)은 가동면의 일측 끝단에서 반대편으로 연장되며, 소정의 폭과 깊이로 절취되어 형성된다. 이러한 펼침멈춤홈(210)의 일부는 원형삽입홈(202)과 겹쳐진다.  The deploying stop groove 210 is formed on the movable surface of the wing drive shaft 200 located in the axial end of the wing drive shaft 200, that is, in the direction of the circumferential direction of the guided vehicle. The deploying stop groove 210 is formed on one side of the movable surface opposite to the other side and cut to a predetermined width and depth. A part of the spreading stopper 210 overlaps with the circular insertion groove 202.

펼침멈춤홈(210) 중 원형삽입홈(202)의 축심으로부터 가동면의 끝단까지 떨어진 일측은 폭의 길이가 바깥쪽으로 갈수록 좁아지는 형태를 가져 후술하게 될 펼침멈춤돌기가 끼일 수 있도록 경사면을 가지는데 이 경사면이 제1지지면(211)이고, 경사면을 가지지 않은 한 쌍의 타측면이 제2지지면(212)이며, 가동면 중 펼침멈춤홈(210)과 원형삽입홈(202)으로 인해 발생된 영역을 제외한 영역이 제3지지면(203)이다.One side of the spreading stop groove 210, which is spaced from the central axis of the circular insertion groove 202 to the end of the movable surface, has a shape in which the width becomes narrower toward the outer side so that the spreading stopper, which will be described later, This inclined surface is a first supporting surface 211 and a pair of other side surfaces having no inclined surface is a second supporting surface 212 and is generated due to the unfolding stop groove 210 and the circular insertion groove 202 in the moving surface And the third supporting surface 203 is the area excluding the region where the first supporting surface 203 is formed.

펼침멈춤돌기(421)는 날개부재(400)가 접힘상태에서 날개전개축(420) 중 날개구동축(200)과 마주한 면에 형성되며, 날개구동축(200)과 마주보는 면은 펼침멈춤돌기면(422)이다. 이때, 날개전개축(420)의 형상은 펼침멈춤돌기(421)와 날개본체(410)에서 연장되는 부위를 제외한 부분은 적어도 일부영역에 곡면부(424)를 가지며, 적어도 날개전개축(420)과 펼침멈춤돌기(421)의 폭은 펼침멈춤홈(210)의 폭보다 소정폭 작게 형성된다.The spreading stopper 421 is formed on a surface facing the wing drive shaft 200 of the wing development shaft 420 in a state where the wing member 400 is folded and a surface facing the wing drive shaft 200 is formed as a wedge- 422). At this time, the shape of the blade expansion shaft 420 has a curved surface portion 424 in at least a part of the portion except for the extension stop projection 421 and a portion extending from the blade body 410, and at least the blade expansion shaft 420, And the width of the spreading stopper 421 is smaller than the width of the spreading stopper 210 by a predetermined width.

또한, 펼침멈춤돌기(421)는 펼침멈춤홈(210)에 삽입되는 선단영역이 타 영역에 비해 좁게 형성되어 펼침멈춤돌기(421)가 펼침멈춤홈(210)에 보다 용이하고 확실하게 삽입될 수 있다. 이러한 펼침멈춤돌기(421)의 선단영역은 선단방향으로 갈수록 폭이 좁도록 경사면을 가지며, 이러한 경사면이 제1지지면(211)에 끼워지는 것으로 날개부재(400)의 펼침상태가 안정적으로 유지되며, 유도비행체의 이동방향으로의 흔들림이 방지되어 전체적으로 펼침상태의 신뢰도가 향상된다.In addition, the spreading stopper 421 is formed so that the tip end region inserted into the spreading stop groove 210 is narrower than other regions, so that the spreading stopper 421 can be inserted into the spreading stop groove 210 more easily and reliably have. The leading end region of the spreading stopper 421 has an inclined surface so that the width of the leading end of the spreading stopper 421 becomes narrower toward the leading end. The inclined surface is fitted to the first supporting surface 211, thereby stably maintaining the spreading state of the wing member 400 , The shaking in the moving direction of the guidance vehicle is prevented, and the reliability of the extended state as a whole is improved.

이와 같은 구성으로 인해, 날개부재(400)는 접힘상태에서 펼침상태로 전환이 가능하다. With such a configuration, the wing member 400 can be switched from the folded state to the unfolded state.

접힘상태에서는 날개부재(400)가 비틀림스프링(321)에 의해 접힘상태로 날개멈춤부(110)에 삽입되어 있다. 이때, 펼침멈춤돌기(421)의 펼침멈춤돌기면(422)이 날개구동축(200)의 제3지지면(203)에 면접하여 지지되도록 펼침멈춤홈(210)은 펼침멈춤돌기(421)와 소정의 각도를 가진다. In the folded state, the wing member 400 is inserted into the wing stopper 110 in a folded state by the torsion spring 321. At this time, the spreading stop groove 421 is formed so as to be in contact with the third support surface 203 of the wing drive shaft 200, and the spreading stop groove 421, .

날개부재(400)를 펼침상태로 전환할 때는 날개구동부는 날개구동축(200)을 회전시켜 날개구동축(200)의 끝단의 가동면이 회전하게 만든다. 이때, 펼침멈춤홈(210) 또한 날개구동축(200)의 회전에 의해 소정의 각도로 회전하여 펼침멈춤돌기(421)와 펼침멈춤홈(210)은 동일한 위치에 마주보게 된다. When the wing member 400 is switched to the unfolded state, the wing driving unit rotates the wing driving shaft 200 to rotate the moving surface of the end of the wing driving shaft 200. At this time, the spreading stopper 210 also rotates at a predetermined angle by rotation of the wing drive shaft 200, so that the spreading stopper 421 and the spreading stopper 210 face each other at the same position.

펼침멈춤돌기(421)와 펼침멈춤홈(210)이 동일한 위치에 마주보게 위치하면 비틀림스프링(321)에 의해 펼침상태 방향으로 미는 힘을 가진 채 접혀있는 날개부재(400)는 탄성력으로 인해 펼침멈춤돌기(421)가 펼침멈춤홈(210)에 삽입되며 펼침상태로 전환된다. 이때, 펼침멈춤돌기면(422)의 일부 영역은 제1지지면(211)과 접촉하여 끼이게 되고, 곡면부(424)의 형상으로 인해 펼침멈춤돌기(421)가 펼침멈춤홈(210) 내에서 회동할 때 간섭이 발생되지 않는다. When the spreading stopper 421 and the spreading stopper 210 are positioned to face each other at the same position, the folded wing member 400 having a pushing force in the direction of the spreading state by the torsion spring 321, The projection 421 is inserted into the unfolding stop groove 210 and is switched to the unfolded state. At this time, a part of the extended stop projection surface 422 comes into contact with the first support surface 211, and the shape of the curved surface portion 424 causes the extended stop projection 421 to slide in the extended stop groove 210 No interference occurs when it is turned on.

이렇게 펼침상태에서는 펼침멈춤돌기면(422)의 일부 영역은 제1지지면(211)에 끼인상태로 지지되고, 펼침멈춤돌기면(422)과 곡면부(424)의 양 측면의 일부 영역은 제1지지면(211)과 제2지지면(212)에 의해 지지된다. 즉, 날개부재(400)의 날개전개축(420)에 형성된 펼침멈춤돌기(421)가 제1지지면(211)에 의해 끼여 지지되는 것으로 인해 날개부재(400)가 펼침상태를 유지하게 되며, 유도비행체의 비행에 따라 날개부재(400)에 걸리는 저항 또한 제1지지면(211)에 의해 지지된다.In this extended state, a part of the extended stop projection surface 422 is held in contact with the first support surface 211, and a part of both sides of the extended stop projection surface 422 and the curved surface portion 424 1 support surface 211 and the second support surface 212. [ That is, the wing member 400 is kept in the unfolded state because the wedge stopper 421 formed on the wing development shaft 420 of the wing member 400 is held by the first support surface 211, The resistance to the wing member 400 is also supported by the first support surface 211 in accordance with the flight of the guidance vehicle.

이렇게 날개부재(400)가 펼침상태로 전환되면 펼침멈춤부로 인해 날개부재(400)의 펼침상태가 유지되는 동시에, 날개부재(400)는 날개구동축(200)과 일체회전가능하게 되어, 날개부재(400)가 펼쳐진 상태에서 날개구동축(200)의 회전량을 조절하는 것으로 날개본체(410)의 회전각도를 조절할 수 있다. 즉, 날개부재(400)가 펼쳐진 상태에서 날개구동부를 이용하여 날개구동축(200)을 회전시켜 날개본체(410)가 공기저항을 원하는 방향으로 받게 하여 유도비행체의 비행거리와 비행방향을 조절할 수 있게 된다.When the wing member 400 is switched to the unfolded state, the unfolded state of the wing member 400 is maintained and the wing member 400 can rotate integrally with the wing drive shaft 200, The rotation angle of the blade main body 410 can be adjusted by adjusting the rotation amount of the blade driving shaft 200 in a state where the blade main body 410 is unfolded. That is, when the wing member 400 is unfolded, the wing drive shaft 200 is rotated using the wing driving unit so that the wing body 410 receives the air resistance in a desired direction so that the flying distance and the flying direction of the induction flight body can be adjusted do.

상기에서 설명한 바와 같이, 본 발명에서는 펼침멈춤돌기(421)가 날개부재(400)의 날개전개축(420)에 형성되고, 펼침멈춤홈(210)은 날개구동축(200)에 형성되는 것을 예로서 설명했지만, 이와 반대로 형성될 수 있고, 펼침멈춤홈(210)과 펼침멈춤돌기(421)의 형상 또한 펼침멈춤돌기(421)가 펼침멈춤홈(210)에 삽입되어 날개부재(400)가 접힘상태에서 펼침상태로 전환되고 펼침상태가 안정적으로 유지되기 위한 다양한 형태를 가질 수 있다.As described above, in the present invention, the spreading stopper 421 is formed on the blade expansion shaft 420 of the wing member 400, and the spreading stop groove 210 is formed on the wing drive shaft 200 as an example The configuration of the spreading stopper groove 210 and the spreading stopper projection 421 is also such that the spreading stopper projection 421 is inserted into the spreading stopper groove 210 so that the winging member 400 is folded To the unfolded state and to maintain the unfolded state stably.

날개구동축(200)과 날개구동부는 다음과 같은 구성으로 날개구동부가 날개구동축(200)을 회전하도록 할 수 있다.The wing driving shaft 200 and the wing driving unit may be configured such that the wing driving unit rotates the wing driving shaft 200 in the following configuration.

날개구동축(200)의 외경에는 날개구동축(200)과 일체회전 하도록 결합되는 웜휠(220)이 설치되고, 날개구동부는 웜휠(220)에 맞물리는 웜기어(512)를 가지는 모터축(511)과 모터축(511)을 회전시키는 구동모터(510) 및 모터축(511)을 지지하는 베어링(520)으로 구성될 수 있다. 이와 같은 구성으로 인해 웜휠(220)과 웜기어(512)의 회전결합으로 구동모터(510)의 빠른 회전속도를 감속시킬 수 있는 효과와, 날개구동축(200)의 회전량을 정확하게 조절할 수 있는 효과가 발생된다.A worm wheel 220 coupled to the worm drive shaft 200 integrally rotates integrally with the worm drive shaft 200. The worm drive unit includes a motor shaft 511 having a worm gear 512 engaged with the worm wheel 220, A drive motor 510 for rotating the shaft 511 and a bearing 520 for supporting the motor shaft 511. [ With this configuration, the rotational speed of the drive motor 510 can be reduced by the rotational coupling between the worm wheel 220 and the worm gear 512, and the effect of accurately controlling the amount of rotation of the wing drive shaft 200 .

본 발명에서의 웜휠(220)과 웜기어(512) 및 구동모터(510)로 날개구동축(200)을 회전시키는 구성을 예시하였지만, 날개구동축(200)을 필요한 만큼 회전 또는 회동시키기 위한 다양한 구성들 중에서 선택 가능하다.The configuration in which the worm drive shaft 200 is rotated by the worm wheel 220, the worm gear 512 and the drive motor 510 in the present invention is exemplified. However, among the various configurations for rotating the worm drive shaft 200 as needed Selectable.

본 발명은 날개부재(400)가 펼침상태를 유지하도록 날개회동지지부재(300)와 날개부재(400) 중 어느 하나에 마련된 고정홈(423)과 다른 하나에 마련되어 고정홈(423)에 상호 맞물리는 고정핀(330)을 가지는 펼침유지부를 더 포함할 수 있다.The present invention is provided in the other one of the fixing grooves 423 provided in any one of the wing pivot support member 300 and the wing member 400 so as to maintain the wing member 400 in the unfolded state, And may further include a spread holding portion having a fixing pin 330. [

도 7은 날개전개축(420)에 고정홈(423)이 설치되고, 날개회동지지부재(300)에 고정핀(330)이 설치된 것을 도시화 하고 있으나, 고정홈(423)과 고정핀(330)은 이와 반대로 형성될 수 있다. 7 shows a state in which the fixing groove 423 is provided on the blade expansion shaft 420 and the fixing pin 330 is installed on the blade rotation supporting member 300. However, Can be formed in the opposite manner.

고정핀(330)은 도시된 바와 같이 날개회동지지부재(300)에 삽입되고 후단이 펼침유지스프링(331)에 의해 날개전개축(420) 방향으로 탄성력을 갖도록 준비된다. 이러한 고정핀(330)은 날개전개축(420)이 접힘상태에서는 탄성력을 가진 채 준비되고, 날개전개축(420)이 펼침상태에서는 고정홈(423)에 삽입되어 날개부재(400)가 펼침상태를 안정적으로 유지하도록 한다.The fixing pin 330 is inserted into the blade pivot support member 300 and the rear end thereof is prepared to have an elastic force in the direction of the blade deployment axis 420 by the unfolding holding spring 331. The fixing pin 330 is prepared while having an elastic force when the vane development shaft 420 is folded and inserted into the fixing groove 423 when the vane development axis 420 is in the unfolded state, .

본 발명은 날개부재(400)가 펼침상태에서 날개구동축(200)과의 일체회전을 더욱 안정적으로 유지하도록 하는 일체회동유지부를 포함할 수 있다. 일체회동유지부는 날개회동지지부재(300)와 날개구동축(200)의 가동면 중 어느 하나에 형성되는 연결홈(240)과 다른 하나에 설치되는 연결핀(340) 및 연결핀(340)에 탄성력을 가하는 연결스프링(341)을 포함한다.The present invention may include an integral pivotal holding portion for maintaining the integral rotation with the wing drive shaft 200 more stably in the extended state of the wing member 400. [ The integral pivotal holding portion is provided with a connecting pin 340 and a connecting pin 340 provided on the other side of the connecting groove 240 formed on one of the vane pivotal support member 300 and the movable surface of the wing driving shaft 200, And a connecting spring 341 for applying a connecting spring 341.

도 8은 날개회동지지부재(300)에 연결핀(340)이 설치되고, 날개구동축(200)의 가동면에 연결홈(240)이 설치된 것을 도시화 하고 있으나, 연결핀(340)과 연결홈(240)은 이와 반대로 형성될 수 있다. 8 shows that the connecting pin 340 is provided on the blade pivot support member 300 and the connecting groove 240 is formed on the moving surface of the blade driving shaft 200. However, 240 may be formed in the opposite manner.

연결핀(340)은 도시된 바와 같이, 날개회동지지부재(300)에 삽입되고 후단에 연결스프링(341)이 설치되어 날개구동축(200)방향으로 탄성력을 가진 채 준비된다. 이러한 연결핀(340)은 펼침물림부의 펼침멈춤홈(210)과 펼침멈춤돌기(421)가 서로 만날 때 연결홈(240)에 삽입되어 날개회동지지부재(300)와 날개구동축(200)이 서로 결합되어 일체회전가능하게 한다. 이때, 펼침상태의 날개부재(400)는 날개회동지지부재(300)에 의해 지지되고, 날개전개축(420)과 날개구동축(200)은 펼침물림부에 의해 일체회전가능하며, 일체회동유지부에 의해 날개회동지지부재(300)와 날개전개축(420)은 보다 안정적으로 인체회전가능하게 된다. 즉, 날개부재(400)가 날개구동축(200)과 보다 안정적으로 일체회전가능하게 유지되어 날개구동축(200)의 회전량에 의해 날개본체(410)의 회전량을 정확하게 조절할 수 있게 된다.The connection pin 340 is inserted into the wing pivot support member 300 and is provided with a connection spring 341 at the rear end thereof and is prepared with elastic force in the direction of the wing drive shaft 200. The connecting pin 340 is inserted into the connecting groove 240 when the spreading stop groove 210 of the spreading part and the spreading stopper 421 meet with each other so that the blade supporting member 300 and the blade driving shaft 200 Thereby making it possible to rotate integrally. At this time, the unfolded wing member 400 is supported by the wing pivot support member 300, the wing deployment shaft 420 and the wing drive shaft 200 are integrally rotatable by the unfolding portion, The swinging pivot support member 300 and the blade deployment shaft 420 can rotate the human body more stably. That is, the wing member 400 can be more stably and integrally rotatable with the wing drive shaft 200, and the amount of rotation of the wing body 410 can be accurately controlled by the amount of rotation of the wing drive shaft 200.

본 발명은 날개부재(400)의 접힘상태와 펼침상태에 따른 회전저항과, 날개부재(400)가 날개구동축(200)과 일체회전할 때의 회전량을 감지하여 회전구동부를 통해 날개구동축(200)을 제어할 수 있도록 하는 회전량감지부를 가진다.The present invention detects the rotational resistance of the wing member 400 in accordance with the folding state and the unfolding state of the wing member 400 and the amount of rotation when the wing member 400 rotates integrally with the wing driving shaft 200, And a rotation amount sensing unit for controlling the rotation angle sensor.

회전량감지부는 날개구동축(200)에 결합되는 섹터기어(230)와, 섹터기어(230)와 결합되어 섹터기어(230)의 이동량에 따라 날개구동축(200)의 회전량을 감지하는 분압기(610)를 포함한다. 섹터기어(230)의 기어부는 날개구동축(200)과 소정거리를 가지고 형성된다. 즉, 날개구동축(200)의 회전반경보다 큰 회전반경을 가질 수 있도록 하여 날개구동축(200)의 회전량보다 큰 회전량을 가진다. The rotation amount sensing unit includes a sector gear 230 coupled to the wing drive shaft 200 and a voltage divider 610 coupled to the sector gear 230 to sense the amount of rotation of the wing drive shaft 200 according to the amount of movement of the sector gear 230. [ ). The gear portion of the sector gear 230 is formed with a predetermined distance from the wing drive shaft 200. That is, the wing drive shaft 200 has a rotation radius larger than the rotation radius of the wing drive shaft 200, and has a rotation amount larger than the rotation amount of the wing drive shaft 200.

분압기(610)는 섹터기어(230)를 통해 날개구동축(200)의 회전저항과 회전량을 감지한다. 날개부재(400)가 접힘상태에서 날개구동축(200)이 회전할 때 발생되는 회전저항보다 날개부재(400)가 펼침상태로 전환되어 날개구동축(200)이 회전할 때 발생되는 회전저항이 더 큰 것을 이용해 분압기(610)는 날개부재(400)가 펼침상태로 전환되었는지 확인가능하고, 높은 회전저항을 가진 상태에서 날개회전축이 회전하여 섹터기어(230)가 움직일 때 날개구동부의 구동모터(510)를 제어하여 날개본체(410)의 회전량을 조절하게 된다.The voltage divider 610 senses the rotational resistance and the amount of rotation of the wing drive shaft 200 through the sector gear 230. The rotational resistance generated when the wing member 400 is changed to the opened state and the wing member driving shaft 200 is rotated is larger than the rotational resistance generated when the wing member 400 is rotated when the wing member 400 is folded, The voltage divider 610 can check whether the wing member 400 has been switched to the extended state and the driving motor 510 of the wing driving unit when the wing rotating shaft rotates and the sector gear 230 moves when the wing member 400 has a high rotational resistance, So that the amount of rotation of the wing body 410 is controlled.

100 지지부재 110 날개멈춤부
200 날개구동축 202 원형삽입홈
203 제3지지면 210 펼침멈춤홈
211 제1지지면 212 제2지지면
220 웜휠 230 섹터기어
240 연결홈 300 날개회동지지부재
302 결합축 310 날개부재삽입홈
311 개방부 312 스프링삽입홈
313 회동핀 313A 비틀림스프링고정홈
321 비틀림스프링 330 고정핀
331 펼침유지스프링 340 연결핀
341 연결스프링 400 날개부재
410 날개본체 420 날개전개축
421 펼침멈춤돌기 422 펼침멈춤돌기면
423 고정홈 424 곡면부
425 회동홈 426 결합핀
510 구동모터 511 모터축
512 웜기어 520 베어링
610 분압기100 support member 110 wing stop
200 wing drive shaft 202 circular insertion groove
203 third support surface 210 spread stop groove
211 first supporting surface 212 second supporting surface
220 worm wheel 230 sector gear
240 connecting groove 300 wing pivot support member
302 coupling shaft 310 wing member insertion groove
311 opening portion 312 spring insertion groove
313 Pivot pin 313A Torsion spring fixing groove
321 Torsion spring 330 Retaining pin
331 unfolding spring 340 connecting pin
341 connecting spring 400 wing member
410 Wing body 420 Wing expansion shaft
421 Spreading stopper 422 Spreading stopper surface
423 fixing groove 424 curved portion
425 rotation groove 426 engagement pin
510 Drive motor 511 Motor shaft
512 Worm gear 520 bearing
610 voltage regulator

Claims (5)

유도비행체의 날개구동장치에 있어서,
상기 유도비행체에 설치되며 날개멈춤부를 갖는 지지부재와,
상기 지지부재에 회전가능하게 설치되는 날개구동축과,
상기 날개구동축을 회전구동하는 날개구동부와,
상기 날개구동축에 대해 상대회동가능하게 설치되는 날개회동지지부재와,
상기 날개구동축의 축선을 따라 연장된 펼침상태와, 상기 축선에 대해 절곡된 접힘상태 간을 회동 가능하도록 상기 날개회동지지부재에 힌지 결합되며 접힘상태에서 날개멈춤부에 의해 상기 날개구동축의 회전방향에 따른 회동이 저지되는 날개부재와,
상기 날개부재를 상기 날개회동지지부재에 대하여 펼침상태 방향으로 탄성적으로 미는 탄성부재와,
상기 날개구동축과 상기 날개부재 중 어느 하나에 마련된 펼침멈춤홈과 다른 하나에 마련되어 상기 펼침멈춤홈에 상호 맞물리도록 마련된 펼침멈춤돌기를 가지며, 상기 날개구동축의 소정의 회전위치에서 상기 펼침멈춤홈과 상기 펼침멈춤돌기가 상호 맞물리며 상기 날개부재가 접힘상태에서 펼침상태로 전환하게 하는 펼침물림부를 포함하는 것을 특징으로 하는 유도비행체의 날개구동장치.In a wing drive device for an induction vehicle,
A support member provided on the guide body and having a wing stop;
A wing drive shaft rotatably installed on the support member,
A blade drive unit for rotatingly driving the wing drive shaft,
A wing pivot support member provided so as to be rotatable relative to the wing drive shaft,
A wing drive shaft which is hinged to the wing pivot support member so as to be rotatable between an unfolded state extending along an axis of the wing drive shaft and a folded state that is bent with respect to the axis, A wing member that is prevented from rotating along its axis,
An elastic member elastically pushing the wing member in the direction of the unfolded state with respect to the wing pivot support member;
And a spreading stop provided on the other one of the spreading stop grooves provided on any one of the wing drive shaft and the wing member and arranged to be interlocked with the spreading stop groove, And the spreading protrusions engage with each other and allow the wing members to change from the folded state to the unfolded state. 제 1항에 있어서,
상기 날개부재의 펼침상태와 접힘상태에 따른 상기 날개구동축의 회전저항과 상기 날개부재가 상기 날개구동축과 일체회전할 때의 회전량을 감지하는 회전량감지부를 가지는 것을 특징으로 하는 유도비행체의 날개구동장치.The method according to claim 1,
And a rotation amount sensing unit for sensing the rotation resistance of the wing drive shaft according to the unfolded state and the collapsed state of the wing member and the rotation amount when the wing member rotates integrally with the wing drive shaft. Device. 제 1항에 있어서,
상기 날개부재가 펼침상태를 유지하도록 상기 날개회동지지부재와 상기 날개부재 중 어느 하나에 마련된 고정홈과 다른 하나에 마련되어 상기 고정홈에 상호 맞물리는 고정핀을 가지는 펼침유지부를 더 포함하는 것을 특징으로 하는 유도비행체의 날개구동장치.The method according to claim 1,
Further comprising a deploying holding part provided on the other of the fixing grooves provided on the wing pivot support member and the wing member so as to maintain the wing member in a unfolded state and having a fixing pin mutually engaged with the fixing groove, A wing drive device of an induction vehicle. 제 1항에 있어서,
상기 펼침멈춤돌기는 상기 펼침멈춤홈에 삽입되는 선단영역이 타 영역에 비해 좁게 형성되는 것을 특징으로 하는 유도비행체의 날개구동장치.The method according to claim 1,
Wherein the deploying stopper has a leading end region inserted into the deploying groove narrower than other regions. 제 1항에 있어서,
상기 날개구동부는 상기 날개구동축과 일체회전하는 웜휠과 상기 웜휠과 맞물리는 웜기어 및 상기 웜기어를 회전시키는 구동모터를 포함하는 것을 특징으로 하는 유도비행체의 날개구동장치.The method according to claim 1,
Wherein the wing drive unit includes a worm wheel that rotates integrally with the wing drive shaft, a worm gear which is engaged with the worm wheel, and a drive motor that rotates the worm gear.
KR1020180000766A 2017-11-22 2018-01-03 Driving device for wing of guided aircraft KR101901892B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
KR1020170156325 2017-11-22
KR20170156325 2017-11-22

Publications (1)

Publication Number Publication Date
KR101901892B1 true KR101901892B1 (en) 2018-09-28

Family

ID=63721759

Family Applications (1)

Application Number Title Priority Date Filing Date
KR1020180000766A KR101901892B1 (en) 2017-11-22 2018-01-03 Driving device for wing of guided aircraft

Country Status (1)

Country Link
KR (1) KR101901892B1 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR102088240B1 (en) 2018-11-14 2020-03-12 주식회사 경인테크 Maneuvering wing drive for guided cannon with easy storage and separation
KR102104259B1 (en) * 2018-12-21 2020-04-24 국방과학연구소 Canard deploying apparatus for guided missile and canard deploying method for guided missile using the same
KR102214443B1 (en) * 2019-11-13 2021-02-09 국방과학연구소 Apparatus for fixing neutral position of wings of projectile and projectile comprising thereof

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR102088240B1 (en) 2018-11-14 2020-03-12 주식회사 경인테크 Maneuvering wing drive for guided cannon with easy storage and separation
KR102104259B1 (en) * 2018-12-21 2020-04-24 국방과학연구소 Canard deploying apparatus for guided missile and canard deploying method for guided missile using the same
KR102214443B1 (en) * 2019-11-13 2021-02-09 국방과학연구소 Apparatus for fixing neutral position of wings of projectile and projectile comprising thereof

Similar Documents

Publication Publication Date Title
KR101901892B1 (en) Driving device for wing of guided aircraft
KR0176320B1 (en) Guided missile wing deployment and fixture
KR101117102B1 (en) Deploying device of folding wing and aircraft having the same
KR101234218B1 (en) Wing device and flight vehicle having the same
CN210041901U (en) Electronic device
KR102223487B1 (en) Fin deployment mechanism for a projectile and method for fin deployment
EP2128370B1 (en) Door closing device and door device provided therewith
CN110832160B (en) Hinge device
KR960704209A (en) MISSILE WITH DEPLOYABLE CONTROL FINS
KR20060025048A (en) Air-vent of a automobile
KR101345669B1 (en) Portable guided missile having unfolding device for wing
JP5134388B2 (en) Lid device
KR101963894B1 (en) Folding Wing Deployment Device of Compact Unmanned Aerial and Launch System having the same
KR20120094968A (en) Door control device coupled with wing deploying and flight vehicle having the same
RU2535789C1 (en) Folding aerodynamic rudder
KR101976720B1 (en) Deployment apparatus of control wing
KR20050113667A (en) A device for slowing the movement of a door, drawer or similar movable member, having releasable locking means
JP7081449B2 (en) Sliding door support device
KR100964986B1 (en) Apparatus for unlocking wing of missile
KR830007363A (en) Rocket aircraft
CN109498089A (en) A kind of hysteroscope stapler steering lock apparatus and the hysteroscope stapler using it
KR101338177B1 (en) Adjustable apparatus for control wing of portable guided missile
EP4095037A1 (en) Drone arms locking/deployment mechanism
KR102081885B1 (en) Unfolding wings apparatus of folding blade
CN109720961A (en) Governor assemblies and elevator device

Legal Events

Date Code Title Description
E701 Decision to grant or registration of patent right
GRNT Written decision to grant