EP3931522A1 - Système de déploiement et de verrouillage d'aile - Google Patents

Système de déploiement et de verrouillage d'aile

Info

Publication number
EP3931522A1
EP3931522A1 EP20712689.7A EP20712689A EP3931522A1 EP 3931522 A1 EP3931522 A1 EP 3931522A1 EP 20712689 A EP20712689 A EP 20712689A EP 3931522 A1 EP3931522 A1 EP 3931522A1
Authority
EP
European Patent Office
Prior art keywords
wing
hinge
spring
deployment
deployed position
Prior art date
Legal status (The legal status 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 status listed.)
Pending
Application number
EP20712689.7A
Other languages
German (de)
English (en)
Inventor
Özer TAGA
Muhammed Emin CERIT
Kemal YAMAN
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Scientific and Technological Research Council of Turkey TUBITAK
Original Assignee
Scientific and Technological Research Council of Turkey TUBITAK
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 Scientific and Technological Research Council of Turkey TUBITAK filed Critical Scientific and Technological Research Council of Turkey TUBITAK
Publication of EP3931522A1 publication Critical patent/EP3931522A1/fr
Pending legal-status Critical Current

Links

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
    • F42B10/16—Wrap-around fins

Definitions

  • the invention relates to wing deployment and locking system in the fields of defence, aviation and aerospace, providing that wings and winglets, that are used for making an object able to fly and remain securely in the air during flight through generating aerodynamic forces, are in a folded position prior to launch, allowing ease of movement and increasing storage efficiency; and are transformed from the folded position into a fully-deployed and locked position when launched, providing an aerodynamic advantage obtained with an extended surface area.
  • the wing deployment mechanisms are used to enable the munition wings/fins to be folded for satisfying the need for the storage of munition in a smaller volume and, when it is launched, to be deployed for getting into flying position.
  • the automatic wing deployment mechanisms in the prior art includes torsion springs and hydraulic actuator mechanisms that are located adjacent to the wings and that allows the wings to be deployed along with firing the munition by making controlled rotational movement until the wings reach a certain wingspan. In the majority of wing deployment systems, wing is opened through its rotation movement around the vertical z-axis extending from the upper part to the lower part of munition.
  • Methods employed in the prior art for locking in the deployed position in order to ensure that the structural integrity is retained and the wings are kept securely in the deployed position against the presence of aerodynamic and aerothermal loads generated during flight in conjunction with the deployment of wings are generally such that the matching holes in the wing root and in the surface on which the wing is fastened are engaged with each other by spring-loaded ring pin or that a tab attached to the wing root in such a way that it protrudes from the wing root is fitted into a recess formed in the flying object’s (such as a missile, rocket etc.) body itself.
  • the prior art document with the patent number US618644B1 discloses a wing deployment and locking system wherein a tapered connection is used.
  • the system includes a wing (400) that is located on a flying object, a base (300) in the shape of an elongated rod on which there are holes allowing the wing to be mounted onto exterior surface of the flying object by screws, arms (303 and 305) protruding from the base, tapered teeth (307 and 309) extending from the side of the arms and being in the form of a tab with a cylindrical hole along an axis parallel to the base, wing bosses (401 and 403) extending from the bottom side of the wing through which the wing and the base are assembled and having a cylindrical cavity along an axis which is identical with the axis of the tapered teeth in the base, tapered slots (405 and 407) that are on the wing bosses and shaped to match with the tapered teeth in the base, a pin (201 ) that is used for joining the wing and the
  • the wing When the flying object onto which the system is mounted is launched by being released from the canister inside which the flying object is stored, the wing begins to open by rotating around the pin through the torque applied by the torsion spring. In the last five degrees remaining before the wing is fully open, tapered slots (405, 407) in the wing bosses and tapered teeth (307,309) in the base begin to mesh with each other. Over the last five degrees, compression spring which is wound around the pin under the torsion spring, having sufficient tension, enables the tapered slots and the tapered teeth to be completely mated with each other by translating the wing bosses linearly along the axis through which the pin passes by a predetermined distance.
  • the foldable wing section is fully deployed in conjunction with the configuration of torsion springs that rotates a splined shaft (24) to which it is connected by means of a gear train (64) along with the release of the configuration of torsion springs loaded in closing position of the foldable wing section when the wing is deployed.
  • the system is designed to be able to operate to a considerable extent independently of temperature variations and reduce the effects of environmental conditions on the performance by using the configuration of torsion springs in lieu of a pyrotechnic wing actuation system for deploying wings.
  • there is a lock linkage which enables the foldable wing section to remain folded until its deployment, and which is connected with both the foldable wing section and the fixed wing section by means of lock pins.
  • the prior art document with the patent number US4884766A relates to a fin deployment system, ensuring that high performance in flight is delivered through reducing aerodynamic drag which hinders the movement of aircraft, and that fin cross section is minimized through mounting of the fin deployment system completely within the flying object for obviating the possibility of being detected by radar by virtue of reducing the radar cross section.
  • a pyrotechnic gas generator that is used in the system as an actuation mechanism for enabling the deployment of the fin in the folded position is connected to a piston (42) and a fin lock mechanism (44) in the folded position.
  • the gas heated by the pyrotechnic gas generator which is ignited electrically or chemically is spread through orifices (50, 52), which not only pushes the piston towards a fin hinge (20) by applying pressure against the base of the piston but also allows the release of the fin by pushing a piston (54) loaded by spring comprised in the lock mechanism in the folded position towards base (60).
  • Grooves (38a) being made on the inner surface of a housing (38) encircling the piston (42) interlock with external splines (66a) on the outer surface of the piston (42), which causes that the piston (42) rotates simultaneously while making a linear movement.
  • Inner splines (66b) on the internal side of the piston (42) slides along straight grooves on a torque shaft enclosed by the piston, which enables the torque shaft and a clutch (18) which is connected to the torque shaft to make only rotational movement.
  • the rotary movement of the piston is transmitted to the fin hinge through the clutch, which pivots the fin spar (16) upward and fully extends the fin.
  • the locking of the fin in the fully deployed position is carried out by enabling a plunger (1 12) to be inserted into a recess on an actuator control shaft (24) while at time same time allowing controlled rotation of the fin along the fin's vertical axis.
  • there is a spring-powered retraction mechanism allowing only the controlled rotation of the fin when the fin comes into the fully-deployed position by disconnecting the clutch from the fin hinge.
  • wings are folded onto the body of a munition for increasing storage efficiency in cases where a munition is stored inside a special canister in an air platform or a tube in a launching platform.
  • the wings which occupy much less volume through being folded before launch and enable obtaining of the same or more aerodynamic surface area through being fully deployed at the time of launching in comparison with the conventional fixed-wing systems wherein the wings are kept fixed rather than being folded, are utilized.
  • the retraction mechanism powered by spring in the prior art systems is provided, in the present invention, with recesses (hinge-1 recess, spring housing recess) and the protrusions (casing protrusion, front hinge-2 protrusion, rear hinge-2 protrusion) that are formed in the parts of the subsystem to which the wing is connected, and matched with each other when the wing comes to the fully deployed position to prevent the rotational movement of the wing.
  • the locking in the fully deployed state is carried out by spring- powered pins being inserted into a housing or a formed surface on the parts providing rotational movement.
  • An object of the invention is to develop a wing deployment and locking system that increases storage efficiency in cases where a munition is stored inside a special canister in an air platform or a tube in a launching platform prior to its launching by reducing the volume occupied by the munition through folding wings onto the body of the munition, and enables to obtain aerodynamic advantage and achieve longer range through the formation of the same or more wing surface area in comparison with the fixed-wing systems by enabling wings to be deployed when launching the munition.
  • Yet another object of the invention is to develop a wing deployment and locking system that do not require an electrical interface, and that minimizes losses stemming from the spacing between the moving parts.
  • Figure 1 Isometric perspective drawing of the wing deployment and locking system for undeployed state (both wing-1 and wing-2 are undeployed in folded state).
  • Figure 2 Wing-1 and integrated wing-1 subsystem.
  • Figure 3 Wing-2 and integrated wing-2 subsystem.
  • FIG. 4 Detailed section drawing of wing-1 subsystem mechanism.
  • FIG. 5 Detailed section drawing of wing-2 subsystem mechanism.
  • Figure 6 Isometric perspective drawing of wing deployment and locking system for only wing-2 is fully deployed.
  • Figure 7 Isometric perspective drawing of the wing deployment and locking system in deployed state (Both wing-1 and wing-2 are fully deployed)
  • FIG 8 Perspective drawings of hinge-1 (3) and casing (6) parts in the wing-1 subsystem.
  • Figure 9 Exploded perspective drawing of wing-2 subsystem.
  • Figure 1 shows the undeployed position of the wing deployment and locking system.
  • FIG. 2 shows the wing-1 (1 ) and the subsystem integrated into wing-1 (1 ) and Figure 3 shows the wing-2 (9) and the subsystem integrated into wing-2 (9).
  • Wing-1 and wing-2 subsystems perform deployed state locking to allow the munition to deploy its wings under aerodynamic loads at the moment of firing and to remain in its deployed position for the duration of the flight.
  • FIG. 4 shows a detailed section drawing of the wing-1 subsystem mechanism.
  • Specially designed pre-stressed machined spring-1 (16) that provides the drive on the system to deploy the wing-1 (1 ), which is fixed to the hinge-1 (3) with the spring pin-1 (5) on one side and fixed to the spring retainer (4) on the other side.
  • Hinge-1 (3) is mounted radially in the spring holder (4) and bearing housing (7), which allows it to make only radial movement on the wing-1 (3) by means of one-way clutch-1 (15) at both ends.
  • Hinge-1 (3) which provides wing-1 (3) to deploy completely by rotating radially, is also limited to the casing (6) part with radial direction to the spring retainer (4) and the bearing housing (7).
  • lock spring-1 (17) and lock pin-1 (19) that perform the locking process to keep it in fully deployed position during the flight duration.
  • cover-1 (2) and cover-2 (8) are placed at the ends of the hinge-1 (3) as shown in Figure 1.
  • Figure 5 shows a detailed section drawing of the wing-2 subsystem mechanism.
  • Specially designed pre-tensioned machined spring-2 (21 ) that provides the drive on the system to deploy the wing-2 (9), on one side fixed to the spring housing (12) with the spring pin-2 (22), on the other side fixed to the front hinge-2 (13).
  • the spring housing (12) is bearing radially to the front hinge-2 (13) and rear hinge-2 (11 ), which allows it to make radial-only movement on two sides of the wing-2 (9) via the one way clutch-2 (20).
  • the lock spring-2 (24) and lock pin-2 (23) performs deployed state locking inside the rear hinge-2 (11 ) to protect this deployed position during flight.
  • Cover-3 (10) shown in Figure 1 is used to hold the lock spring-2 (24) stuck in the rear hinge-2 (11 ) and also cover-4 (14) in the end part of the front hinge-2 (13) is used to provide the system with all its need.
  • FIG 6 shows a perspective drawing for deployed position of only wing-2 (9) in the deploying and locking system.
  • Undeployed state of wing 2 (9) shown in Figure 1 becomes deployed as shown in Figure 6 with the fire of munition as a result of releasing of the machined spring-2 (21 ), which is initially in the torsion-state, in the wing-2 subsystem mechanism shown in Figure 5.
  • the spring pin-2 (22) and the spring housing (12) which is connected to each other rotates radially with the rotation movement of the machined spring-2 (21 ) so that it is provided to deploy the wing-2 (9).
  • the one-way clutch-1 (15) and one-way clutch-2 (20) in the wing-1 subsystem mechanism and wing-2 subsystem mechanism that are shown respectively in Figure 4 and Figure 5 have the ability to meet the aerodynamic loads that may come in the opposite direction to the system and to prevent the return movement of the system.
  • connection interfaces with holes for bolt coupling are available on the spring housing (12), front hinge-2 (13) and rear hinge-2 (1 1 ) to connect between the wings and their subsystems by mounting hinge-1 (3) to wing-1 (1 ), by mounting spring housing (12) to wing-2 (9), by mounting front hinge-2 (13) and rear hinge-2 (11 ) to hinge-1 (3).
  • the wing deployment and locking system which is the subject matter of the invention, can be used in all flying objects where the wing and winglet systems are used to enable the object to fly and remain on air while being subjected to the aerodynamic forces by generating a lifting force, and guide the object by providing it with maneuverability.
  • the volume requirement is to be reduced by folding the wings onto the munition body before firing, when the munition used is stored inside a canister in an air platform or a tube of the launching platform, thus increasing the firepower by carrying more munitions simultaneously and achieving a longer range along with providing aerodynamic advantages through creating more surface area in a lower volume compared to a fixed wing.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Closing And Opening Devices For Wings, And Checks For Wings (AREA)

Abstract

La présente invention concerne un système de déploiement et de verrouillage d'aile, qui améliore l'efficacité de stockage en réduisant le volume occupé par la munition par pliage des ailes sur le corps de munition dans le cas où la munition est stockée à l'intérieur d'une cartouche spéciale dans la plateforme d'air ou le tube de la plateforme de lancement avant le tir, ce qui permet d'atteindre une plage plus longue par l'avantage aérodynamique obtenu suite à la création d'une ou plusieurs zones de surface d'aile par rapport aux systèmes d'ailes fixes classiques, en assurant le déploiement des ailes au moment du tir lorsque la munition quitte le tube dans lequel elle est stockée. Le système comprend une aile 1 (1) et une aile 2 (9) créant une zone de surface aérodynamique, et des mécanismes de sous-système qui permettent aux ailes de se déployer et de rester verrouillées dans l'état déployé pendant le vol. Le sous-système d'aile 1 est essentiellement constitué : d'un ressort usiné 1 (16), qui fournit l'entraînement requis avec une production de couple élevé au système par le tir d'un boulon pyrotechnique (18), d'une charnière 1 (3), qui assure le déploiement de l'aile 1 (1) en effectuant un mouvement de rotation radial par un embrayage unidirectionnel 1 (15) situé aux deux extrémités, et d'un ressort de verrouillage 1 (17) et d'une goupille de verrouillage 1 (19) assurant le verrouillage du système lorsque l'aile 1 (1) arrive à la position complètement déployée. Le sous-système d'aile 2 est essentiellement constitué : d'un ressort usiné 2 (21), qui est dans l'état de torsion lorsque le système est dans sa position non déployée, d'un logement de ressort (12), qui permet le déploiement de l'aile 2 (9) par réalisation d'un mouvement de rotation radial par un embrayage unidirectionnel 2 (20) situé aux deux extrémités grâce au couple élevé fourni par le ressort usiné 2 (21) lorsque la munition est relâchée au moment du tir, d'un ressort de verrouillage 2 (24) et d'une goupille de verrouillage 2 (23) assurant le verrouillage lorsque l'aile 2 (9) est dans sa position complètement déployée.
EP20712689.7A 2019-02-28 2020-02-28 Système de déploiement et de verrouillage d'aile Pending EP3931522A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
TR2019/03055A TR201903055A2 (tr) 2019-02-28 2019-02-28 Kanat açma ve ki̇li̇tleme si̇stemi̇
PCT/IB2020/051709 WO2020174448A1 (fr) 2019-02-28 2020-02-28 Système de déploiement et de verrouillage d'aile

Publications (1)

Publication Number Publication Date
EP3931522A1 true EP3931522A1 (fr) 2022-01-05

Family

ID=69846518

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20712689.7A Pending EP3931522A1 (fr) 2019-02-28 2020-02-28 Système de déploiement et de verrouillage d'aile

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EP (1) EP3931522A1 (fr)
TR (1) TR201903055A2 (fr)
WO (1) WO2020174448A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112124564B (zh) * 2020-09-17 2022-04-01 西安电子科技大学 一种基于发射筒的固定翼无人机折叠机构
CN112665468B (zh) * 2020-12-21 2023-08-15 兰州空间技术物理研究所 一种新型强锁定弱解锁机构
CN113682496B (zh) * 2021-07-30 2024-04-26 长沙天仪空间科技研究院有限公司 一种航天飞行器的工装结构
CN115342692A (zh) * 2022-09-12 2022-11-15 四川航浩科技有限公司 抗高量级冲击的折叠翼同步展开可靠锁定机构

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US618644A (en) 1899-01-31 Cotton-seed roaster
FR929040A (fr) * 1946-06-14 1947-12-15 Dispositif pour le repliement et le déploiement d'ailettes de mobiles empennés
DE2649643A1 (de) * 1976-10-29 1978-06-15 Messerschmitt Boelkow Blohm Raketengetriebener flugkoerper mit entfaltbaren stabilisierungsflaechen
US4691880A (en) 1985-11-14 1987-09-08 Grumman Aerospace Corporation Torsion spring powered missile wing deployment system
US4884766A (en) 1988-05-25 1989-12-05 The United States Of America As Represented By The Secretary Of The Air Force Automatic fin deployment mechanism
FR3068094B1 (fr) * 2017-06-26 2019-08-02 Mbda France Piece de liaison pivot destinee a un engin volant ou a un systeme pour engin volant, en particulier un missile
KR101833682B1 (ko) * 2017-08-04 2018-03-02 국방과학연구소 토션바를 이용한 접힘 날개를 가진 발사체의 날개 전개 장치 및 전개 방법

Also Published As

Publication number Publication date
TR201903055A2 (tr) 2020-09-21
WO2020174448A1 (fr) 2020-09-03

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