WO2011087189A1 - Door control device coupled with wing deployment and flight vehicle having the same - Google Patents

Door control device coupled with wing deployment and flight vehicle having the same Download PDF

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Publication number
WO2011087189A1
WO2011087189A1 PCT/KR2010/003756 KR2010003756W WO2011087189A1 WO 2011087189 A1 WO2011087189 A1 WO 2011087189A1 KR 2010003756 W KR2010003756 W KR 2010003756W WO 2011087189 A1 WO2011087189 A1 WO 2011087189A1
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WO
WIPO (PCT)
Prior art keywords
door
wing
state
main body
locking bar
Prior art date
Application number
PCT/KR2010/003756
Other languages
English (en)
French (fr)
Inventor
Woo Yong Lee
Sang Hun Shin
Heon Suk Hong
Original Assignee
Agency For Defense Development
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 Agency For Defense Development filed Critical Agency For Defense Development
Publication of WO2011087189A1 publication Critical patent/WO2011087189A1/en

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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

Definitions

  • the present invention relates to relates to a door control device for a flight vehicle, capable of controlling a door in connection with wing deployment, and a flight vehicle having the same.
  • a flight vehicle (flight, flying object) is provided with wings for stable flight.
  • wings which are folded within a fuselage in a launch tube may be deployed out of the fuselage at an appropriate flying time point after coming out of the launch tube.
  • openings for allowing the wing deployment should be present at an outer surface of the fuselage whereas such openings should be closed after the wing deployment to maintain aerodynamic characteristics during flight. Accordingly, a consecutive outer surface of the guided missile may be achieved, and doors for closing the openings are provided at the guide missiles.
  • an object of the present invention is to provide a door control device for a flight vehicle capable of geometrically setting a time point of closing a door and a flight vehicle having the same.
  • Another object of the present invention is to provide a door control device for a flight vehicle, capable of being operated in a simple manner and having high operation reliability, and a flight vehicle having the same.
  • a door control device for a flight vehicle, the door control device including, an opening formed at a main body of the flight vehicle and allowing a corresponding wing to be deployed from inside to outside of the main body, a door installed at the main body to be rotatable between a first state where the opening is open and a second state where the opening is closed, an elastic unit configured to apply an elastic force to the door such that the door rotates from the first state to the second state, and a door locking unit configured to lock the door in the first state, and, when the wing is deployed, unlock the door responsive to the deployment of the wing such that the door rotates to the second state.
  • the wing may be deployed by rotation, and the locking bar may be disposed in parallel to a rotation surface of the wing.
  • the contact pin may penetrate through the rotation surface.
  • the wing may be configured such that a front end thereof is locked at the contact pin in a rotating direction of the wing during the deployment.
  • the door locking unit may further include a spring configured to apply an elastic force to the locking bar in a direction toward the holder.
  • the door may include a door main body and a holder.
  • the door main body may be formed to correspond to the opening and supported by the elastic unit.
  • the holder may be formed in a direction intersecting with the door main body, and locked by at least part of the door locking unit in the first state so as to lock the door.
  • the door may be coupled to the main body by a hinge, and the elastic unit may be configured to generate a torsional moment based upon a central axis of the hinge-coupling.
  • a flight vehicle provided with a flight vehicle main body, a wing deployed from inside to outside of the main body through an opening formed at an outer surface of the main body, and a door, the flight vehicle including a door control device configured to rotate the door, responsive to deployment of the wing, between a first state where the opening is open and a second state where the opening is closed.
  • the door locking unit which is unlocked due to being stopped at the wing, allows a geometrical setting of an optimal time point of closing the door according to how much the wing is deployed.
  • the door control device for the flight vehicle which is constructed more simply and have high operation reliability can be realized.
  • FIGS. 2 to 4 are an operation view, a front view and a side view respectively showing a door control device in a first state
  • FIGS. 5 to 7 are an operation view, a front view and a side view respectively showing the door control device in a state where a wing is being deployed;
  • FIGS. 8 to 10 are an operation view, a front view and a side view respectively showing the door control device in a second state.
  • FIG. 1 is an overview of a flight vehicle 100 in accordance with one embodiment of the present invention.
  • FIG. 1 exemplarily shows a guide missile as one example of the flight vehicle 100.
  • the flight vehicle 100 may include a main body 110, wings 120 and a door control device 200.
  • the main body 110 may be configured to be flown by a propulsive force, and include a front part 111, a middle part 112 and a rear part 113.
  • the front part 111 may be located at a front side in a proceeding direction of the main body 110, and configured in a streamlined form.
  • the middle part 112 may be connected to the front part 111 and have at least part thereof with a predetermined circular section.
  • the rear part 113 may be formed at an opposite side to the front part 111 by interposing the middle part 112 therebetween.
  • the rear part 113 may be provided with the wings 120 which render the main body 110 run in one direction.
  • the wings 120 may be aligned at a preset interval along a circumference of the main body 110. Such alignment allows the flight vehicle 100 to be kept stably going straight ahead.
  • the present invention may not be limited to the alignment.
  • the wings 120 may be located at the middle part 112 or located across the middle part 112 and the rear part 113.
  • the wings 120 may be deployed from inside to outside of the main body 110 via openings 130 (see FIG. 3) formed through an outer surface of the main body 110. That is, each wing 120 which was folded within the main body 110 is outwardly deployed through the opening 130 when the main body is launched.
  • the door control device 200 may include a door 211 which is rotatably installed at the main body 110.
  • the door control device 200 may rotate the door 211, responsive to the deployment of the wing 120, from a first state where the door 211 opens the opening 130 to a second state where the door 211 closes the opening 130.
  • the door control device 200 may include a door 211, an elastic unit 212 and a door locking unit 220.
  • the door 211 may be formed to correspond to the opening 130, and rotatable between the first state and the second state so as to open and close the opening 130.
  • the elastic unit 212 may apply an elastic force to the door 211 such that the door 211 can rotate from the first state to the second state.
  • the door 211 may be coupled to the main body 110 by a hinge, and the elastic unit 212 may generate a torsional moment based upon a central axis of the hinge-coupling.
  • the elastic unit 212 may be a torsion spring, for example.
  • the door main body 211a may be formed to correspond to the opening 130. That is, the shape and area of the door main body 211a may be the same or similar to the shape and area of the opening 130 which is required to unfold the wing 120.
  • the door main body 211a may be supported by the elastic unit 212. Accordingly, an elastic force is applied to the door main body 211a in a rotating direction from the first state to the second state.
  • the door main body 211a is not shown in each operation view for the sake of explanation.
  • the holder 211b may be formed in a direction intersecting with the door main body 211a, and locked by at least part of the door locking unit 220 in the first state so as to lock the door 211.
  • the door locking unit 220 may lock the door 211 in the first state, and, when the wing 120 is deployed, unlock the door 211 responsive to the deployment of the wing 120 such that the door 211 rotates to the second state.
  • the door locking unit 220 may be implemented by a plurality of elements mounted at the holder 211b and the main body 110. Hereinafter, configurations of those elements will be described.
  • the holder 211b may extend from the door 211 such that one end of the locking bar 222 is inserted therein in the first state.
  • the holder 211b may be provided with a through hole in which the locking bar 222 is inserted, accordingly, the rotation of the door 211 in a diameter direction of the through hole can be restricted due to the insertion of the locking bar 222.
  • the locking bar 222 may be formed long in one direction to be slidably mounted at the main body 110.
  • a support bearing 224 may further be provided so as to support the locking bar 222.
  • FIGS. 2 to 4 show that the wing 120 is folded within the main body 110 and the door 211 opens the opening 130, namely, the aforesaid first state.
  • a torsional moment is applied in a closing direction of the door 211 due to the elastic unit 212 located at the hinge-coupled portion of the door 211; however, the locking bar 222 is inserted into the through hole of the holder 211b which is integrally assembled or formed with the door 211, such that the door 211 is restricted from being moved.
  • the door locking unit 220 may include a spring 225, which is configured to apply an elastic force toward the holder 211b of the locking bar 222.
  • the locking bar 222 is inserted into the spring 225, and the spring 225 may be a compression spring for supporting part of the locking bar 222. The compression spring pushes the locking bar 222 such that the locking bar 222 is not escaped from the holder 211b.
  • FIGS. 5 to 7 show a partially (approximately 75°) deployed state of the wing 120, which show a time point when a front surface of the wing 120 starts contacting the contact pin 223.
  • the wing 120 is deployed by rotation, and the locking bar 222 is aligned in parallel to the rotation surface of the wing 120. Also, the contact pin 223 penetrates through the rotation surface.
  • the wing 120 may also be formed such that a front side thereof (i.e., a front surface of the wing 120) is locked at the contact pin 223 in a rotating direction of the wing 120 during deployment of the wing 120.
  • FIGS. 8 to 10 show a completely deployed state of the wing 120 out of the main body 110, which show that the door 211 blocks the opening 130, namely, the aforesaid second state.
  • the contact pin 223 is moved by being pushed by the front end of the wing 120 responsive to the deployment of the wing 120, and the locking bar 222 integrally formed with the contact pine 223 is completely escaped from the holder 211b. Accordingly, the locking force by which the door 211 is locked in the open state is released. Consequently, the door 211 is closed by the elastic force of the elastic unit 212 mounted at the hinge-coupled portion of the door 211.
  • the door control device for the flight vehicle and the flight vehicle having the same according to the present invention may not be limited to the construction and method illustrated in the foregoing embodiments. Many variations can be embodied by selective combination of all or part of the embodiments.
  • the door control device for the flight vehicle and the flight vehicle having the same may be industrially applicable.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Power-Operated Mechanisms For Wings (AREA)
  • Lock And Its Accessories (AREA)
PCT/KR2010/003756 2010-01-15 2010-06-11 Door control device coupled with wing deployment and flight vehicle having the same WO2011087189A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
KR10-2010-0004075 2010-01-15
KR1020100004075A KR101181275B1 (ko) 2010-01-15 2010-01-15 날개 전개와 연동된 비행체의 도어 제어장치 및 이를 구비하는 비행체

Publications (1)

Publication Number Publication Date
WO2011087189A1 true WO2011087189A1 (en) 2011-07-21

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/KR2010/003756 WO2011087189A1 (en) 2010-01-15 2010-06-11 Door control device coupled with wing deployment and flight vehicle having the same

Country Status (2)

Country Link
KR (1) KR101181275B1 (ko)
WO (1) WO2011087189A1 (ko)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014203237A3 (en) * 2013-06-16 2016-02-25 Rafael Advanced Defense Systems Ltd. Shutter mechanism for covering a wing deployment opening
CN109502009A (zh) * 2018-12-11 2019-03-22 湖北航天飞行器研究所 一种飞行器折叠翼锁定机构

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105730674B (zh) * 2016-02-02 2018-09-14 玉环天润航空机械制造有限公司 开合机构、锁及直升机
KR101688951B1 (ko) * 2016-07-29 2016-12-22 국방과학연구소 날개 대칭전개 장치 및 이를 구비하는 비행체
KR102231030B1 (ko) * 2019-10-30 2021-03-23 국방과학연구소 경사진 전방 접힘 날개의 전개 성능을 예측하는 방법
RU2770959C1 (ru) * 2021-12-24 2022-04-25 Акционерное общество "Машиностроительное конструкторское бюро "Факел" имени академика П.Д. Грушина Механизм раскрытия и стопорения аэродинамического руля

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5899410A (en) * 1996-12-13 1999-05-04 Mcdonnell Douglas Corporation Aerodynamic body having coplanar joined wings
US6260797B1 (en) * 1998-01-13 2001-07-17 Science Applications International Corporation Transformable gun launched aero vehicle
US6446906B1 (en) * 2000-04-06 2002-09-10 Versatron, Inc. Fin and cover release system
US6880780B1 (en) * 2003-03-17 2005-04-19 General Dynamics Ordnance And Tactical Systems, Inc. Cover ejection and fin deployment system for a gun-launched projectile

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5899410A (en) * 1996-12-13 1999-05-04 Mcdonnell Douglas Corporation Aerodynamic body having coplanar joined wings
US6260797B1 (en) * 1998-01-13 2001-07-17 Science Applications International Corporation Transformable gun launched aero vehicle
US6446906B1 (en) * 2000-04-06 2002-09-10 Versatron, Inc. Fin and cover release system
US6880780B1 (en) * 2003-03-17 2005-04-19 General Dynamics Ordnance And Tactical Systems, Inc. Cover ejection and fin deployment system for a gun-launched projectile

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014203237A3 (en) * 2013-06-16 2016-02-25 Rafael Advanced Defense Systems Ltd. Shutter mechanism for covering a wing deployment opening
US10358205B2 (en) 2013-06-16 2019-07-23 Rafael Advanced Defense Systems Ltd. Shutter mechanism for covering a wing deployment opening
CN109502009A (zh) * 2018-12-11 2019-03-22 湖北航天飞行器研究所 一种飞行器折叠翼锁定机构
CN109502009B (zh) * 2018-12-11 2022-06-07 湖北航天飞行器研究所 一种飞行器折叠翼锁定机构

Also Published As

Publication number Publication date
KR101181275B1 (ko) 2012-09-11
KR20120094968A (ko) 2012-08-28

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