WO2009127789A1 - Pylon for attachment to an aircraft wing, for example, under an airplane wing - Google Patents
Pylon for attachment to an aircraft wing, for example, under an airplane wing Download PDFInfo
- Publication number
- WO2009127789A1 WO2009127789A1 PCT/FR2008/000527 FR2008000527W WO2009127789A1 WO 2009127789 A1 WO2009127789 A1 WO 2009127789A1 FR 2008000527 W FR2008000527 W FR 2008000527W WO 2009127789 A1 WO2009127789 A1 WO 2009127789A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- wing
- pylon
- fixing
- main body
- yoke
- Prior art date
Links
- 210000005069 ears Anatomy 0.000 claims description 5
- 230000035939 shock Effects 0.000 abstract description 6
- 238000010008 shearing Methods 0.000 abstract 1
- 239000003350 kerosene Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D7/00—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
- B64D7/08—Arrangements of rocket launchers or releasing means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/06—Rocket or torpedo launchers for rockets from aircraft
Definitions
- the present invention relates to a pylon intended to be fixed on an aircraft wing, for example under an aircraft wing, in particular to support a load.
- An object of the present invention is therefore to solve the problem mentioned above with a solution that is simple to implement, reliable and inexpensive.
- the present invention relates to a pylon intended to be fixed on an aircraft wing, for example under an aircraft wing, in particular to support a load, said pylon comprising a main body and fastening means to said wing, characterized in that the fastening means have a programmed shear zone designed to break in the event of shock exceeding a determined intensity of the pylon against an obstacle so that said pylon disengages from the wing.
- the device according to the present invention may furthermore comprise at least one of the following characteristics:
- the body (21) comprises two half-shells (21a, 21b) joining in a longitudinal joint plane;
- the main body has the general shape of a parallelepiped, and the attachment means are provided at the front and rear ends of the main body side facing the wing, the shear zone being provided on front and / or rear attachment means;
- the rear attachment means comprise a fixing yoke fixed on the main body by means of screws each provided with a zone of least resistance;
- the front attachment means comprise a fixing yoke fixed on the main body by means of screws each provided with a zone of least resistance;
- the fixing screws of the front yoke are divided into two groups arranged in two directions perpendicular to each other, a first direction transverse to the joint plane of the main body (21) and a second longitudinal direction relative thereto;
- the front fixing yoke and the rear fixing yoke each have at least one hinge for fixing under the wing;
- the front fixing yoke is articulated under the wing with the aid of two pairs of protruding ears provided with respective orifices intended to receive a shaft, the orifices of the first pair of ears being perpendicular to the parting plane, while that the orifices of the second pair being parallel to said joint plane;
- the rear fixing yoke is articulated under the wing with a pair of prominent ears provided with orifices parallel to the joint plane and intended to receive a shaft; and the tower further comprises, opposite the connecting means, means for fixing a load such as a nacelle refueling, a tank or a military load.
- FIG. 1 is a perspective view of a pylon according to the present invention. invention mounted under a wing and carrying a load
- Figure 2 is a perspective view of the pylon of Figure 1
- - Figure 3 is a side view of the pylon
- Figure 4 is a top view of the tower.
- Figure 1 shows an aircraft wing portion 10 under which is fixed a pylon 20 according to the present invention and intended to support a load such as a missile or a kerosene tank.
- the pylon 20 is generally parallelepipedal in shape and comprises a main body 21 constituted by two half-shells 21a and 21b joining in a longitudinal joint plane 22.
- the main body 21 is provided with a means of fixing the load 5 and the attachment means 30 to the wing 10.
- the attachment means 30 are divided into front attachment means 40 and attachment means rear 50, all arranged on an upper connecting side 23 of the main body 21 facing the wing 10.
- the front attachment means 40 comprise a front fixing yoke 41 fixed to the main body 21 by means of fixing screws 45.
- Each fixing screw 45 is provided with a zone of least resistance (not shown ) designed to break in case of shock exceeding a determined intensity of the tower 20 against an obstacle so that said pylon 20 disengages from the wing 10.
- This zone of least resistance is embodied for example by a radial notch shaped "V "Having dimensions (depth width, angle V) calculated for this shock breaks said screws at this region particularly weakened mechanically.
- the fixing screws 45 are divided into two groups 45a and 45b arranged in two directions perpendicular to each other.
- a first group 45a of fixing screw 45 extends in a direction perpendicular to the joint plane 22 while a second group 45b of fixing screw 45 extends in a direction parallel to said joint plane 23, as shown in Figure 2. From this way, the front fixing cap 41 encloses the two half-shells 21a and 21b.
- the front fixing yoke 41 has joints for fixing it to the wing 10.
- it comprises two pairs of lugs 46 and 47 which are traversed by respective orifices 46a and 47a intended to receive shafts engaged with means standardized support of the wing (not shown).
- the orifices 46a and 47a are perpendicular to one another, the orifice 46a extending perpendicularly to the joint plane 22 while the orifice 47a extending longitudinally with respect to the main body 21 along the joint plane 22.
- the rear attachment means 50 comprise a rear fixing yoke 51 fixed to the main body 21 by means of fixing screws 55.
- Each fixing screw 55 is provided with a zone of least resistance (not shown) provided for to break in the event of shock exceeding a determined intensity of the pylon 20 against an obstacle so that said pylon 20 disengages from the wing 10.
- This zone of least resistance is materialized for example by a radial notch shaped "V" having dimensions (depth width, angle V) calculated for this shock breaks said screws at this area particularly weakened mechanically.
- the fastening screws 55 are distributed in pairs of two screws for each half-shell and are arranged parallel to the joint plane 22.
- the rear fixing yoke 51 has a hinge for fixing it to the wing 10.
- it comprises a pair of lugs 56 traversed by the respective orifices 56a intended to receive a shaft engaged with standardized support means of the yoke. wing (not shown).
- the orifices 56a extend longitudinally with respect to the main body 21, along the joint plane 22.
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Vibration Dampers (AREA)
Abstract
The present invention relates to a pylon (20) for attachment to an aircraft wing, for example, under an airplane wing, particularly to carry a load, said pylon (20) including a main body (21) and an attaching means (30) for attachment to said wing; and is characterized in that the attaching means (30) has a shearing area expected to break in case of shock exceeding a predetermined force of the pylon (20) against an obstacle such that said pylon (20) separates from the wing.
Description
PYLONE DESTINE A ETRE . . FIXE SUR UNE VOILURE D'AERONEF,PYLONE INTENDED TO BE . . FIXED ON AN AIRCRAFT VESSEL,
PAR EXEMPLE SOUS UNE AILE D'AVIONFOR EXAMPLE UNDER A FLIGHT WING
La présente invention concerne un pylône destiné à être fixé sur une voilure d'aéronef, par exemple sous une aile d'avion, afin notamment de supporter une charge .The present invention relates to a pylon intended to be fixed on an aircraft wing, for example under an aircraft wing, in particular to support a load.
Actuellement, en particulier dans le domaine des avions de combat, il est courant de fixer certaines charges, telles que des armes, des équipements militaires divers ou un réservoir de ravitaillement, sous les ailes. Pour cela, il est généralement fait appel à l'utilisation d'un pylône intermédiaire de support qui relie cette charge à la voilure de l'avion. Ce pylône est couramment relié à l'aile par des composants mécaniques spécifiques dimensionnés pour respecter certaines exigences et résister à des contraintes liées notamment aux vibrations et à la fatigue des matériauxCurrently, particularly in the field of fighter jets, it is customary to set certain charges, such as weapons, various military equipment or a refueling tank, under the wings. For this, it is generally used the use of an intermediate support pylon that connects this load to the wing of the aircraft. This pylon is commonly connected to the wing by specific mechanical components sized to meet certain requirements and to withstand the constraints related to vibration and fatigue of materials
Or, en cas de choc sur le sol d'une piste d'atterrissage, ou en cas de crash de l'avion, des forces extrêmement importantes sont engendrées sur la charge et le pylône. Ces forces, dirigées pour la plupart vers l'arrière et le bas de l'appareil, provoquent très souvent l'arrachement de l'aile sous laquelle la charge est fixée.However, in case of impact on the ground of an airstrip, or in case of crash of the aircraft, extremely high forces are generated on the load and the pylon. These forces, directed for the most part towards the rear and the bottom of the apparatus, very often provoke the tearing of the wing under which the load is fixed.
Un but de la présente invention est donc de résoudre le problème cité précédemment à l'aide d'une solution simple à mettre en œuvre, fiable et peu coûteuse.An object of the present invention is therefore to solve the problem mentioned above with a solution that is simple to implement, reliable and inexpensive.
Ainsi, la présente invention a pour objet un pylône destiné à être fixé sur une voilure d'aéronef, par exemple sous une aile d'avion, afin notamment de supporter une charge, ledit pylône comprenant un corps principal et des moyens d'attache à ladite voilure, caractérisé en ce que les moyens d'attache présentent une zone de cisaillement programmée prévue pour se rompre en cas de choc dépassant une intensité déterminée du pylône contre un obstacle afin que ledit pylône se désolidarise de la voilure.Thus, the present invention relates to a pylon intended to be fixed on an aircraft wing, for example under an aircraft wing, in particular to support a load, said pylon comprising a main body and fastening means to said wing, characterized in that the fastening means have a programmed shear zone designed to break in the event of shock exceeding a determined intensity of the pylon against an obstacle so that said pylon disengages from the wing.
Selon des modes de réalisation préférés, le dispositif selon la présente invention peut comprendre en outre l'une au moins des caractéristiques suivantes :According to preferred embodiments, the device according to the present invention may furthermore comprise at least one of the following characteristics:
- le corps (21) comporte deux demi coquilles (21a, 21b) se rejoignant en un plan de joint longitudinal ; le corps principal présente la forme générale d'un parallélépipède, et les moyens d'attache sont prévus aux extrémités avant et arrière du côté du corps principal faisant face à la
voilure, la zone de cisaillement étant prévue sur des moyens d' attache avant et/ou arrière ; les moyens d'attache arrière comportent une chape de fixation fixée sur le corps principal par l'intermédiaire de vis munies chacune d'une zone de moindre résistance ;- The body (21) comprises two half-shells (21a, 21b) joining in a longitudinal joint plane; the main body has the general shape of a parallelepiped, and the attachment means are provided at the front and rear ends of the main body side facing the wing, the shear zone being provided on front and / or rear attachment means; the rear attachment means comprise a fixing yoke fixed on the main body by means of screws each provided with a zone of least resistance;
- les moyens d'attache avant comprennent une chape de fixation fixée sur le corps principal par l'intermédiaire de vis munies chacune d'une zone de moindre résistance ;- The front attachment means comprise a fixing yoke fixed on the main body by means of screws each provided with a zone of least resistance;
- les vis de fixation de la chape avant sont réparties en deux groupes disposés selon deux directions perpendiculaires entre elles, une première direction transversale par rapport au plan de joint du corps principal (21) et une seconde direction longitudinale par rapport à ce dernier ;- The fixing screws of the front yoke are divided into two groups arranged in two directions perpendicular to each other, a first direction transverse to the joint plane of the main body (21) and a second longitudinal direction relative thereto;
- la chape de fixation avant et la chape de fixation arrière présentent chacune au moins une articulation pour leur fixation sous la voilure ;- The front fixing yoke and the rear fixing yoke each have at least one hinge for fixing under the wing;
- la chape de fixation avant est articulée sous la voilure à l'aide de deux paires d'oreilles proéminentes munies d'orifices respectifs destinés à recevoir un arbre, les orifices de la première paire d'oreilles étant perpendiculaires au plan de joint, tandis que les orifices de la seconde paire étant parallèle audit plan de joint ;the front fixing yoke is articulated under the wing with the aid of two pairs of protruding ears provided with respective orifices intended to receive a shaft, the orifices of the first pair of ears being perpendicular to the parting plane, while that the orifices of the second pair being parallel to said joint plane;
- la chape de fixation arrière est articulée sous la voilure à l'aide d'une paire d'oreilles proéminentes munies d'orifices parallèles au plan de joint et destinés à recevoir un arbre ; et le pylône comporte en outre, à l'opposé des moyens de liaison, des moyens de fixation d'une charge telle qu'une nacelle de ravitaillement, un réservoir ou une charge militaire.- The rear fixing yoke is articulated under the wing with a pair of prominent ears provided with orifices parallel to the joint plane and intended to receive a shaft; and the tower further comprises, opposite the connecting means, means for fixing a load such as a nacelle refueling, a tank or a military load.
L'invention va maintenant être décrite plus en détail en référence à des modes de réalisation particuliers donnés à titre d'illustration uniquement et représentés sur les figures annexées dans lesquelles : la figure 1 est une vue en perspective d'un pylône conforme à la présente invention monté sous une aile et portant une charge ;
la figure 2 est une vue en perspective du pylône de la figure 1 ; - la figure 3 est une vue de côté du pylône ; et la figure 4 est une vue de dessus du pylône . La figure 1 représente une portion d'aile d'avion 10 sous laquelle est fixé un pylône 20 conforme à la présente invention et destiné à supporter une charge 5 telle qu'un missile ou un réservoir de kérosène .The invention will now be described in more detail with reference to particular embodiments given by way of illustration only and shown in the appended figures in which: FIG. 1 is a perspective view of a pylon according to the present invention. invention mounted under a wing and carrying a load; Figure 2 is a perspective view of the pylon of Figure 1; - Figure 3 is a side view of the pylon; and Figure 4 is a top view of the tower. Figure 1 shows an aircraft wing portion 10 under which is fixed a pylon 20 according to the present invention and intended to support a load such as a missile or a kerosene tank.
Comme cela est visible sur la figure 2, le pylône 20 est de forme générale parallélépipédique et comporte un corps principal 21 constitué par deux demi coquilles 21a et 21b se rejoignant en un plan de joint longitudinal 22. Le corps principal 21 est muni de moyen de fixation 25 de la charge 5 et de moyens d'attache 30 à l'aile 10. Comme cela est visible sur les figures 2 à 4, les moyens d'attache 30 se divisent en moyens d'attache avant 40 et moyens d'attache arrière 50, tous disposés sur un côté supérieur de liaison 23 du corps principal 21 faisant face à l'aile 10.As can be seen in FIG. 2, the pylon 20 is generally parallelepipedal in shape and comprises a main body 21 constituted by two half-shells 21a and 21b joining in a longitudinal joint plane 22. The main body 21 is provided with a means of fixing the load 5 and the attachment means 30 to the wing 10. As can be seen in FIGS. 2 to 4, the attachment means 30 are divided into front attachment means 40 and attachment means rear 50, all arranged on an upper connecting side 23 of the main body 21 facing the wing 10.
Plus précisément, les moyens d'attache avant 40 comprennent une chape de fixation avant 41 fixée sur le corps principal 21 par l'intermédiaire de vis de fixation 45. Chaque vis de fixation 45 est munie d'une zone de moindre résistance (non représentée) prévue pour se rompre en cas de choc dépassant une intensité déterminée du pylône 20 contre un obstacle afin que ledit pylône 20 se désolidarise de l'aile 10. Cette zone de moindre résistance est matérialisée par exemple par une encoche radiale en forme de « V » présentant des dimensions (profondeur largeur, angle du V) calculées pour que ce choc rompe lesdites vis au niveau de cette zone particulièrement affaiblie mécaniquement. Les vis de fixation 45 sont réparties en deux groupes 45a et 45b disposés selon deux directions perpendiculaires entre elles. Un premier groupe 45a de vis de fixation 45 s'étend selon une direction perpendiculaire au plan de joint 22 tandis qu'un second groupe 45b de vis de fixation 45 s'étend selon une direction parallèle audit plan de joint 23, comme cela est représenté sur la figure 2. De
cette façon, la chape de fixation avant 41 enserre les deux demi coquilles 21a et 21b.More specifically, the front attachment means 40 comprise a front fixing yoke 41 fixed to the main body 21 by means of fixing screws 45. Each fixing screw 45 is provided with a zone of least resistance (not shown ) designed to break in case of shock exceeding a determined intensity of the tower 20 against an obstacle so that said pylon 20 disengages from the wing 10. This zone of least resistance is embodied for example by a radial notch shaped "V "Having dimensions (depth width, angle V) calculated for this shock breaks said screws at this region particularly weakened mechanically. The fixing screws 45 are divided into two groups 45a and 45b arranged in two directions perpendicular to each other. A first group 45a of fixing screw 45 extends in a direction perpendicular to the joint plane 22 while a second group 45b of fixing screw 45 extends in a direction parallel to said joint plane 23, as shown in Figure 2. From this way, the front fixing cap 41 encloses the two half-shells 21a and 21b.
Par ailleurs, la chape de fixation avant 41 présente des articulations pour sa fixation sous l'aile 10. Pour cela, elle comporte deux paires oreilles 46 et 47 traversés par des orifices respectifs 46a et 47a destinés à recevoir des arbres en prise avec des moyens de support normalisés de l'aile (non représentés) . Comme cela est visible sur les figure 2 et 4, les orifices 46a et 47a sont perpendiculaires entre eux, l'orifice 46a s 'étendant perpendiculairement au plan de joint 22 tandis que l'orifice 47a s' étendant longitudinalement par rapport au corps principal 21, le long du plan de joint 22.Furthermore, the front fixing yoke 41 has joints for fixing it to the wing 10. For this purpose, it comprises two pairs of lugs 46 and 47 which are traversed by respective orifices 46a and 47a intended to receive shafts engaged with means standardized support of the wing (not shown). As can be seen in FIGS. 2 and 4, the orifices 46a and 47a are perpendicular to one another, the orifice 46a extending perpendicularly to the joint plane 22 while the orifice 47a extending longitudinally with respect to the main body 21 along the joint plane 22.
Les moyens d'attache arrière 50 comportent une chape de fixation arrière 51 fixée sur le corps principal 21 par l'intermédiaire de vis de fixation 55. Chaque vis de fixation 55 est munie d'une zone de moindre résistance (non représentée) prévue pour se rompre en cas de choc dépassant une intensité déterminée du pylône 20 contre un obstacle afin que ledit pylône 20 se désolidarise de l'aile 10. Cette zone de moindre résistance est matérialisée par exemple par une encoche radiale en forme de « V » présentant des dimensions (profondeur largeur, angle du V) calculées pour que ce choc rompe lesdites vis au niveau de cette zone particulièrement affaiblie mécaniquement. Les vis de fixation 55 sont réparties par paire de deux vis pour chaque demi coquille et sont disposées parallèlement au plan de joint 22.The rear attachment means 50 comprise a rear fixing yoke 51 fixed to the main body 21 by means of fixing screws 55. Each fixing screw 55 is provided with a zone of least resistance (not shown) provided for to break in the event of shock exceeding a determined intensity of the pylon 20 against an obstacle so that said pylon 20 disengages from the wing 10. This zone of least resistance is materialized for example by a radial notch shaped "V" having dimensions (depth width, angle V) calculated for this shock breaks said screws at this area particularly weakened mechanically. The fastening screws 55 are distributed in pairs of two screws for each half-shell and are arranged parallel to the joint plane 22.
Par ailleurs, la chape de fixation arrière 51 présente une articulation pour sa fixation sous l'aile 10. Pour cela, elle comporte une paires oreilles 56 traversés des orifices respectifs 56a destinés à recevoir un arbre en prise avec des moyens de support normalisés de l'aile (non représentés) . Comme cela est visible sur les figure 2 et 4, les orifices 56a s'étendent longitudinalement par rapport au corps principal 21, le long du plan de joint 22.Furthermore, the rear fixing yoke 51 has a hinge for fixing it to the wing 10. For this purpose, it comprises a pair of lugs 56 traversed by the respective orifices 56a intended to receive a shaft engaged with standardized support means of the yoke. wing (not shown). As can be seen in FIGS. 2 and 4, the orifices 56a extend longitudinally with respect to the main body 21, along the joint plane 22.
Il va de soi que la description détaillée de l'objet de l'Invention, donnée uniquement à titre d'illustration, ne constitue en aucune manière une limitation, les équivalents techniques étant également compris dans le champ de la présente invention.
It goes without saying that the detailed description of the subject of the invention, given solely by way of illustration, does not in any way constitute a limitation, the technical equivalents also being included in the scope of the present invention.
Claims
1. Pylône (20) destiné à être fixé sur une voilure d'aéronef (10) , par exemple sous une aile d'avion, afin notamment de supporter une charge (5) , ledit pylône (20) comprenant un corps principal (21) et des moyens d'attache (30) à ladite voilure (10) , caractérisé en ce que les moyens d'attache (30) présentent une zone de cisaillement programmée prévue pour se rompre en cas de choc dépassant une intensité déterminée du pylône (20) contre un obstacle afin que ledit pylône (20) se désolidarise de la voilure (10) .1. Pylon (20) intended to be fixed on an aircraft wing (10), for example under an aircraft wing, in particular for supporting a load (5), said pylon (20) comprising a main body (21) ) and fastening means (30) to said wing (10), characterized in that the fastening means (30) have a programmed shear zone intended to break in the event of impact exceeding a given intensity of the pylon ( 20) against an obstacle so that said pylon (20) disengages from the wing (10).
2. Pylône selon la revendication 1, caractérisé en ce que le corps (21) comporte deux demi coquilles (21a, 21b) se rejoignant en un plan de joint longitudinal (22) .2. Pylon according to claim 1, characterized in that the body (21) comprises two half-shells (21a, 21b) joining in a longitudinal joint plane (22).
3. Pylône selon la revendication 2, caractérisé en ce que le corps principal (21) présente la forme générale d'un parallélépipède, et que les moyens d'attache (30) sont prévus aux extrémités avant et arrière du côté (23) du corps principal (21) faisant face a la voilure (10) , la zone de cisaillement étant prévue sur les moyens d'attache avant (40) et/ou arrière (50) . 3. Pylon according to claim 2, characterized in that the main body (21) has the general shape of a parallelepiped, and the attachment means (30) are provided at the front and rear ends of the side (23) of the main body (21) facing the wing (10), the shear zone being provided on the front attachment means (40) and / or rear (50).
4. Pylône selon la revendication 2 ou 3, caractérisé en ce que les moyens d'attache arrière (50) comportent une chape de fixation (51) fixée sur le corps principal (21) par l'intermédiaire de vis (55) munies chacune d'une zone de moindre résistance.4. Pylon according to claim 2 or 3, characterized in that the rear attachment means (50) comprise a fixing yoke (51) fixed on the main body (21) by means of screws (55) each provided with an area of least resistance.
5. Pylône selon l'une quelconque des revendications 2 à 4, caractérisé en ce que les moyens d'attache avant (40) comprennent une chape de fixation (41) fixée sur le corps principal (21) par l'intermédiaire de vis (45) munies chacune d'une zone de moindre résistance.5. Pylon according to any one of claims 2 to 4, characterized in that the front attachment means (40) comprise a fixing yoke (41) fixed on the main body (21) by means of screws ( 45) each provided with a zone of least resistance.
6. Pylône selon la revendication 5, caractérisé en ce que les vis de fixation (45) de la chape avant (41) sont réparties en deux groupes (45a, 45b) disposés selon deux directions perpendiculaires entre elles, une première direction transversale par rapport au plan dé joint (22) du corps principal (21) et une seconde direction longitudinale par rapport à ce dernier. 6. Pylon according to claim 5, characterized in that the fixing screws (45) of the front yoke (41) are divided into two groups (45a, 45b) arranged in two directions perpendicular to each other, a first transverse direction relative to at the joint plane (22) of the main body (21) and a second longitudinal direction relative thereto.
7. Pylône selon l'une quelconque des revendications 2 à 6, caractérisé en ce que la chape de fixation avant (41) et la chape de fixation arrière (51) présentent chacune au moins une articulation pour leur fixation sous la voilure (10) .7. Pylon according to any one of claims 2 to 6, characterized in that the front fixing yoke (41) and the yoke of rear binding (51) each have at least one hinge for fixing under the wing (10).
8. Pylône selon la revendication 7, caractérisé en ce que la chape de fixation avant (41) est articulée sous la voilure (10) à l'aide de deux paires (46, 47) d'oreilles proéminentes munies d'orifices respectifs (46a, 47a) destinés à recevoir un arbre, les orifices (46a) de la première paire d'oreilles (46) étant perpendiculaires au plan de joint (22) , tandis que les orifices8. Pylon according to claim 7, characterized in that the front fixing yoke (41) is articulated under the wing (10) by means of two pairs (46, 47) of protruding ears provided with respective orifices ( 46a, 47a) for receiving a shaft, the orifices (46a) of the first pair of lugs (46) being perpendicular to the joint plane (22), while the orifices
(47a) de la seconde paire (47) étant parallèle audit plan de joint (22) .(47a) of the second pair (47) being parallel to said joint plane (22).
9. Pylône selon la revendication 7 ou 8, caractérisé en ce que la chape de fixation arrière (51) est articulée sous la voilure (10) à l'aide d'une paire (56) d'oreilles proéminentes munies d'orifices (56a) parallèles au plan de joint (22) et destinés à recevoir un arbre .9. Pylon according to claim 7 or 8, characterized in that the rear fixing yoke (51) is articulated under the wing (10) by means of a pair (56) of protruding ears provided with orifices ( 56a) parallel to the joint plane (22) and intended to receive a shaft.
10. Pylône selon l'une quelconque des revendications précédentes, caractérisé en ce qu'il comporte en outre, à l'opposé des moyens de liaison (30) , des moyens de fixation (25) d'une charge10. Pylon according to any one of the preceding claims, characterized in that it further comprises, opposite the connecting means (30), means (25) for fixing a load
(5) telle qu'une nacelle de ravitaillement, un réservoir ou une charge militaire. (5) such as a refueling basket, tank or military load.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/FR2008/000527 WO2009127789A1 (en) | 2008-04-15 | 2008-04-15 | Pylon for attachment to an aircraft wing, for example, under an airplane wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/FR2008/000527 WO2009127789A1 (en) | 2008-04-15 | 2008-04-15 | Pylon for attachment to an aircraft wing, for example, under an airplane wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2009127789A1 true WO2009127789A1 (en) | 2009-10-22 |
Family
ID=40129085
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/FR2008/000527 WO2009127789A1 (en) | 2008-04-15 | 2008-04-15 | Pylon for attachment to an aircraft wing, for example, under an airplane wing |
Country Status (1)
| Country | Link |
|---|---|
| WO (1) | WO2009127789A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106155075A (en) * | 2016-08-22 | 2016-11-23 | 上海交通大学 | A kind of detachable unmanned aerial vehicle control system |
| US10266273B2 (en) | 2013-07-26 | 2019-04-23 | Mra Systems, Llc | Aircraft engine pylon |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2856224A (en) * | 1955-06-02 | 1958-10-14 | Pastushin Aviat Corp | Means for mounting jettisonable stores on aircraft |
| US4155522A (en) * | 1977-07-14 | 1979-05-22 | The Boeing Company | Overload release apparatus for aircraft landing gear or the like |
| EP0144265A1 (en) * | 1983-11-29 | 1985-06-12 | R. ALKAN & Cie. | Aircraft external load suspension and release unit with triple escapement rockers |
| US6679452B1 (en) * | 2002-10-10 | 2004-01-20 | The Boeing Company | Aircraft landing gear support assemblies and associated methods of installation |
| WO2004092011A1 (en) * | 2003-04-09 | 2004-10-28 | Raytheon Company | Fixture for mounting weapons, and method of using |
-
2008
- 2008-04-15 WO PCT/FR2008/000527 patent/WO2009127789A1/en active Application Filing
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2856224A (en) * | 1955-06-02 | 1958-10-14 | Pastushin Aviat Corp | Means for mounting jettisonable stores on aircraft |
| US4155522A (en) * | 1977-07-14 | 1979-05-22 | The Boeing Company | Overload release apparatus for aircraft landing gear or the like |
| EP0144265A1 (en) * | 1983-11-29 | 1985-06-12 | R. ALKAN & Cie. | Aircraft external load suspension and release unit with triple escapement rockers |
| US6679452B1 (en) * | 2002-10-10 | 2004-01-20 | The Boeing Company | Aircraft landing gear support assemblies and associated methods of installation |
| WO2004092011A1 (en) * | 2003-04-09 | 2004-10-28 | Raytheon Company | Fixture for mounting weapons, and method of using |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10266273B2 (en) | 2013-07-26 | 2019-04-23 | Mra Systems, Llc | Aircraft engine pylon |
| CN106155075A (en) * | 2016-08-22 | 2016-11-23 | 上海交通大学 | A kind of detachable unmanned aerial vehicle control system |
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