FR2713591A1 - Automatic release and locking of light or ultra light aircraft landing gear - Google Patents

Automatic release and locking of light or ultra light aircraft landing gear Download PDF

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Publication number
FR2713591A1
FR2713591A1 FR9315266A FR9315266A FR2713591A1 FR 2713591 A1 FR2713591 A1 FR 2713591A1 FR 9315266 A FR9315266 A FR 9315266A FR 9315266 A FR9315266 A FR 9315266A FR 2713591 A1 FR2713591 A1 FR 2713591A1
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FR
France
Prior art keywords
arms
spring
landing gear
aircraft
light
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.)
Granted
Application number
FR9315266A
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French (fr)
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FR2713591B1 (en
Inventor
Cavanna Renzo
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Individual
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Individual
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Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to FR9315266A priority Critical patent/FR2713591B1/en
Publication of FR2713591A1 publication Critical patent/FR2713591A1/en
Application granted granted Critical
Publication of FR2713591B1 publication Critical patent/FR2713591B1/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/08—Undercarriages non-fixed, e.g. jettisonable
    • B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/08—Undercarriages non-fixed, e.g. jettisonable
    • B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
    • B64C25/12—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
    • B64C2025/125—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways into the fuselage, e.g. main landing gear pivotally retracting into or extending out of the fuselage
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F2236/00—Mode of stressing of basic spring or damper elements or devices incorporating such elements
    • F16F2236/02—Mode of stressing of basic spring or damper elements or devices incorporating such elements the stressing resulting in flexion of the spring

Abstract

Two vertically moving arms (1,2) which are pivoted from the aircraft structure (3,4) carry the wheel axle (5). A metallic coiled spring (7) is mounted between the junction point of the two arms and a reinforcing point (8) of the aircraft structure. The arms are held in their low position by the spring compression force which opposes landing gear closing forces arising from landing and rolling. There is a gas shock absorber at the upper part of the spring. The landing gear is raised by a traction rod (10) acting at the junction point of the arms. This rod generates a pull which tips the arms as well as a force perpendicular to the major axis of the spring through a projection (11). This causes buckling and bending of the spring and its complete refolding.

Description

DISPOSITIF DE SORTIE AUTOMATIQUE ET DE VERROUILLAGE EN POSITION SORTIE
POUR TRAIN D'ATTERRISSAGE D'AERONEFS LEGERS ET ULTRA LEGERS
MOTORISES;
La présente invention concerne un dispositif destiné a permettre la sortie automatique ainsi que le verrouillage en position sortie de trains d'atterrissage d'aéronefs légers et ultra légers motorisés.AUTOMATIC EXIT AND LOCKING DEVICE IN EXIT POSITION
FOR LIGHT AND ULTRA LIGHT AIRCRAFT LANDING GEAR
MOTORIZED;
The present invention relates to a device intended to allow automatic exit as well as locking in the exit position of landing gear of light and ultra light motorized aircraft.

De très nombreux dispositifs destinés a assurer la sortie et la rentrée du train d'atterrissage d'avions et d'aéronefs légers et ultra légers ont été décrits; cependant un problème crucial se pose en ce qui concerne les aéronefs ultra légers, c'est celui de l'encombrement et, en corollaire, du poids généralement excessif de ces systèmes.Numerous devices intended to ensure the exit and re-entry of the landing gear of airplanes and light and ultra light aircraft have been described; however, a crucial problem arises with regard to ultra-light aircraft, that of space and, as a corollary, of the generally excessive weight of these systems.

Le dispositif selon l'invention présente l'avantage de remédier a ces inconvénients en combinant une grande simplicité technique, un très faible encombrement et un poids réduit au minimum tout en conservant la rigidité et la fiabilité nécessaires.The device according to the invention has the advantage of overcoming these drawbacks by combining great technical simplicity, a very small footprint and a weight reduced to a minimum while retaining the necessary rigidity and reliability.

Le dispositif selon l'invention comporte en effet selon une première caractéristique, un ressort métallique a spires jointives qui quand il est soumis a des efforts de compression se comporte comme un tube métallique du mème diamètre, pouvant servir de bras de force dans la triangulation destinée a maintenir le train sorti.The device according to the invention in fact comprises, according to a first characteristic, a metal spring with contiguous turns which when it is subjected to compression forces behaves like a metal tube of the same diameter, which can serve as a force arm in the triangulation intended to keep the train out.

Selon une seconde caractéristique, ce ressort peut subir une poussée latérale perpendiculaire a son grand axe de façon a provoquer un flambage et permettre avec un faible effort le pliage complet de l'appareil.According to a second characteristic, this spring can undergo a lateral thrust perpendicular to its major axis so as to cause buckling and allow with little effort the complete folding of the device.

Selon un mode particulier de réalisation, la partie supérieure du ressort constituant le bras de force du dispositif peut comporter une partie d'amortissement sous forme de vérin a gaz.According to a particular embodiment, the upper part of the spring constituting the force arm of the device may include a damping part in the form of a gas spring.

Les dessins annexés illustrent la présente invention.The accompanying drawings illustrate the present invention.

La figure 1 représente de face le dispositif suivant l'invention.Figure 1 shows the device of the invention from the front.

La figure 2 représente de profil le dispositif suivant l'invention.Figure 2 shows in profile the device according to the invention.

La figure 3 représente le dispositif en position fermée: train rentré.Figure 3 shows the device in the closed position: gear retracted.

La figure 4 représente un mode particulier de réalisation.FIG. 4 represents a particular embodiment.

En référence à ces dessins, le dispositif comporte un bras antérieur (1) et un bras postérieur (2); ces deux bras étant fixés à la structure de l'aéronef en des points destinés à recevoir la fixation du train d'atterrissage par l'intermédiaire d'articulations (3) et (4) permettant d'assurer un mouvement vertical de ces bras.With reference to these drawings, the device comprises an anterior arm (1) and a posterior arm (2); these two arms being fixed to the structure of the aircraft at points intended to receive the fixing of the landing gear by means of articulations (3) and (4) making it possible to ensure vertical movement of these arms.

Les deux bras (1) et (2) se rejoignent pour former l'axe de roulement (5) qui portera la roue (6).The two arms (1) and (2) meet to form the rolling axis (5) which will carry the wheel (6).

Un ressort métallique à spires jointives (7) fixé, d'une part au point de jonction des bras (1) et (2), et, d'autre part à la structure de l'aéronef, en un endroit (8) prévu pour supporter les efforts de poussée lors du roulage et des atterrissages, sert de jambe de force pour maintenir ouvert le dispositif.A metallic spring with contiguous turns (7) fixed, on the one hand to the junction point of the arms (1) and (2), and, on the other hand to the structure of the aircraft, in a place (8) provided to support the thrust forces during taxiing and landings, serves as a strut to keep the device open.

Dans la forme de réalisation selon la figure (4), le système comporte, dans la partie supérieure du ressort (7) une partie d'amortissement (9) sous forme d'un verin à gaz. In the embodiment according to Figure (4), the system comprises, in the upper part of the spring (7) a damping part (9) in the form of a gas cylinder.

Dans sa position fermée (train rentré), tel qu'illustré dans la figure (3), le ressort (7) est replié sur lui même et se trouve dans un espace réservé à cet usage dans la paroi latérale de l'aéronef.In its closed position (retracted train), as illustrated in FIG. (3), the spring (7) is folded back on itself and is located in a space reserved for this use in the side wall of the aircraft.

Le dispositif de relevage comporte un élément de traction (10) agissant au point de jonction des bras (1) et (2) mettant en jeu, outre la traction destinée à faire basculer les deux bras, une force exercée perpendiculairement au grand
axe du ressort par l'intermédiairw d'une saillie (11) afin de produire un
flambage et d'amorcer la pliure dudit ressort qui, dès lors ne présentera plus
qu'une très faible résistance pour être amené à sa position complètement
repliée.The lifting device comprises a traction element (10) acting at the junction point of the arms (1) and (2) bringing into play, in addition to the traction intended to tilt the two arms, a force exerted perpendicular to the large
axis of the spring through a projection (11) to produce a
buckling and initiate the bending of said spring which, from then on will no longer present
that a very weak resistance to be brought to its position completely
folded up.

La sortie du train s'effectuera automatiquement par simple relâchement de
l'élément de traction (10) et dés lors que le train sera sorti, le ressort (7) se
trouvera soumis a des efforts de compression le long de son grand axe et
deviendra l'élément indéformable assurant le verrouillage du train en position
sortie pour l'atterrissage et le roulage de l'aéronef. The train will exit automatically by releasing the
the traction element (10) and as soon as the train is out, the spring (7)
will be subjected to compressive forces along its long axis and
will become the non-deformable element ensuring the locking of the train in position
exit for landing and taxiing.

Claims (6)

REVENDICATIONS.CLAIMS. 1) Dispositif pour assurer la sortie et le verrouillage en position sortie du train d'atterrissage d'aéronefs et en particulier d'aéronefs légers et ultra légers motorisés caractérisé en ce que l'élément essentiel assurant la sortie automatique et le verrouillage et position sortie du train est un ressort métallique (7) faisant office de bras de force et maintenant par sa rigidité longitudinale les deux bras pivotants (1) et (2), portant l'axe de la roue,(5), en position basse.1) Device for ensuring the exit and locking in the extended position of the landing gear of aircraft and in particular of light and ultra-light motorized aircraft characterized in that the essential element ensuring the automatic exit and the locking and extended position of the train is a metal spring (7) acting as a force arm and now by its longitudinal rigidity the two pivoting arms (1) and (2), carrying the axis of the wheel, (5), in the low position. 2) Dispositif selon la revendication (1) caractérisé en ce que le ressort métallique (7) est à spires jointives.2) Device according to claim (1) characterized in that the metal spring (7) has contiguous turns. 3) Dispositif selon l'une quelconque des revendications précédentes, caractérisé en ce que la partie supérieure du ressort métallique peut recevoir un amortisseur (9) de type verin a gaz..3) Device according to any one of the preceding claims, characterized in that the upper part of the metal spring can receive a shock absorber (9) of the gas cylinder type. 4) Dispositif caractérisé en ce que deux bras (1) et ('2) mobiles verticalement sont ancrés dans la structure de l'aéronef et se rejoignent pour porter l'axe de roulement (5) du train d'atterrissage.4) Device characterized in that two arms (1) and ('2) movable vertically are anchored in the structure of the aircraft and meet to carry the rolling axis (5) of the landing gear. 5) Dispositif selon les revendications (1) et (2) caractérisé en ce que le ressort métallique (7) est monté entre le point de jonctions des bras mobiles et un point renforcé de la structure de l'aéronef (8) situé au dessus de l'ancrage des deux bras; le ressort faisant office de bras de force et subissant des efforts de compression en s'opposant à la fermeture du train..5) Device according to claims (1) and (2) characterized in that the metal spring (7) is mounted between the point of junctions of the movable arms and a reinforced point of the structure of the aircraft (8) located above anchoring the two arms; the spring acting as a force arm and undergoing compression forces by opposing the closing of the train. 6) Dispositif selon la revendication (5), caractérisé en ce que le dispositif de relevage du train comporte un élément de traction (10) agissant au point de jonction des bras mobiles (1) et (2) , mettant en jeu, outre la traction destinée à faire basculer les deux bras supportant le train, une force exercée perpendiculairement au grand axe du ressort par l'intermédiaire d'une saillie (11) afin de produire un flambage du ressort et amener ce dernier à sa position entièrement repliée.. 6) Device according to claim (5), characterized in that the train lifting device comprises a traction element (10) acting at the junction point of the movable arms (1) and (2), bringing into play, in addition to the traction intended to tilt the two arms supporting the train, a force exerted perpendicular to the long axis of the spring by means of a projection (11) in order to produce a buckling of the spring and bring the latter to its fully folded position.
FR9315266A 1993-12-13 1993-12-13 Automatic exit and locking device in the extended position for landing gear of light and ultra light motorized aircraft. Expired - Fee Related FR2713591B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR9315266A FR2713591B1 (en) 1993-12-13 1993-12-13 Automatic exit and locking device in the extended position for landing gear of light and ultra light motorized aircraft.

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR9315266A FR2713591B1 (en) 1993-12-13 1993-12-13 Automatic exit and locking device in the extended position for landing gear of light and ultra light motorized aircraft.

Publications (2)

Publication Number Publication Date
FR2713591A1 true FR2713591A1 (en) 1995-06-16
FR2713591B1 FR2713591B1 (en) 1997-04-18

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Application Number Title Priority Date Filing Date
FR9315266A Expired - Fee Related FR2713591B1 (en) 1993-12-13 1993-12-13 Automatic exit and locking device in the extended position for landing gear of light and ultra light motorized aircraft.

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FR (1) FR2713591B1 (en)

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE705796C (en) * 1937-02-14 1941-05-10 Kronprinz Akt Ges Fuer Metalli Aircraft chassis
US4300440A (en) * 1977-05-23 1981-11-17 Holter John W Ventilating hatch assembly

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE705796C (en) * 1937-02-14 1941-05-10 Kronprinz Akt Ges Fuer Metalli Aircraft chassis
US4300440A (en) * 1977-05-23 1981-11-17 Holter John W Ventilating hatch assembly

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FR2713591B1 (en) 1997-04-18

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Effective date: 20110923