FR2564582A1 - On-board device for monitoring the load of an aeroplane - Google Patents
On-board device for monitoring the load of an aeroplane Download PDFInfo
- Publication number
- FR2564582A1 FR2564582A1 FR8407752A FR8407752A FR2564582A1 FR 2564582 A1 FR2564582 A1 FR 2564582A1 FR 8407752 A FR8407752 A FR 8407752A FR 8407752 A FR8407752 A FR 8407752A FR 2564582 A1 FR2564582 A1 FR 2564582A1
- Authority
- FR
- France
- Prior art keywords
- rod
- rocket
- load
- axle
- supports
- 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.)
- Withdrawn
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01G—WEIGHING
- G01G19/00—Weighing apparatus or methods adapted for special purposes not provided for in the preceding groups
- G01G19/02—Weighing apparatus or methods adapted for special purposes not provided for in the preceding groups for weighing wheeled or rolling bodies, e.g. vehicles
- G01G19/07—Weighing apparatus or methods adapted for special purposes not provided for in the preceding groups for weighing wheeled or rolling bodies, e.g. vehicles for weighing aircraft
Abstract
Description
Dispositif embarqué de contrôle de la charge d'un avion
L'invention concerne un dispositif embarqué de contrôle de la charge d'un avion, permettant, avant le décollage, de assurer que la charge est bien répartie. Ce dispositif est disposé sur chaque fusée de train d'atterrissage et doit fournir une indication fiable lorsque l'avion est au repos.On-board aircraft load control device
The invention relates to an on-board device for controlling the load of an aircraft, making it possible, before takeoff, to ensure that the load is well distributed. This device is placed on each landing gear rocket and must provide a reliable indication when the airplane is at rest.
Il est connu, pour chaque train d'atterrissage d'un avion, de détecter l'enfoncement des amortisseurs hydrauliques. Ce système est sujet à blocage lorsque l'avion est au repos, et il est nécessaire de faire rouler l'avion au sol pour s'affranchir de ce blocage. Ce système est relativement peu précis et il n'est utilisable qu'en sécurité avant le décollage. It is known, for each landing gear of an aircraft, to detect the sinking of the hydraulic shock absorbers. This system is subject to blockage when the aircraft is at rest, and it is necessary to roll the aircraft on the ground to overcome this blockage. This system is relatively imprecise and it can only be used safely before takeoff.
Il est également connu de mesurer la déformation des fusées en fonction de la charge, au moyen de jauges de contrainte ou de jauges extensométriques placées sur une fibre haute et sur une fibre basse de la fusée. Ce système est fiable mais il exige un étalonnage fréquent. It is also known to measure the deformation of rockets as a function of the load, by means of strain gauges or strain gauges placed on a high fiber and on a low fiber of the rocket. This system is reliable but it requires frequent calibration.
Comme les fusées prennent une certaine flèche lorsque l'avion est chargé, il est également connu de disposer en bout d'arbre un accéléromètre pour détecter la variation correspondante de la verticale. Ce système est acceptable mais il arrive, en fonction de certaines conformations de fusées, que l'inclinaison du plan d'une roue ne corresponde.pas de façon régulière à la charge supportée par le train d'atterrissage. As rockets take a certain deflection when the aircraft is loaded, it is also known to have an accelerometer at the end of the shaft to detect the corresponding variation in the vertical. This system is acceptable but it happens, depending on certain conformations of rockets, that the inclination of the plane of a wheel does not correspond.pas regularly to the load supported by the landing gear.
L'un des buts de l'invention est de proposer un système de contrôle qui n'affecte pas les qualités mécaniques des fusées en introduisant des contraintes supplémentaires, et qui permette une mesure exacte de la charge supportée sans nécessiter un ré-étalonnage fréquent. One of the aims of the invention is to propose a control system which does not affect the mechanical qualities of rockets by introducing additional constraints, and which allows an exact measurement of the load supported without requiring frequent recalibration.
La présente invention a pour objet un dispositif embarqué de contrôle de la charge d'un avion, utilisable sur chaque fusée de train d'atterrissage, caractérisé en ce qu'il comporte : dans l'axe de la fusée, une tige rigide, non soumise à déformation ; et dans le plan vertical de cette tige, deux capteurs inductifs solidaires de la fusée et disposés de part et d'autre de la partie centrale de la tige pour assurer une détection différentielle des variations de la position relative de la tige et de la fusée afin d'en déduire la charge appliquée à la fusée. The present invention relates to an on-board device for controlling the load of an airplane, usable on each landing gear rocket, characterized in that it comprises: in the axis of the rocket, a rigid rod, not subject to deformation; and in the vertical plane of this rod, two inductive sensors secured to the rocket and arranged on either side of the central part of the rod to ensure differential detection of variations in the relative position of the rod and the rocket in order deduce the load applied to the rocket.
Selon d'autres caractéristiques de l'invention
- la tige est portée par deux supports fins , susceptibles de se déformer sans imposer de déformation corrélative à la tige
- chacun des supports est droit et disposé selon un diamètre de la fusée;
- chacun des supports est en forme de S;
- chacun des capteurs inductifs est muni d'un noyau solidaire de la fusée;
- la tige porte un noyau pour influencer les capteurs inductifs.According to other features of the invention
- the rod is carried by two fine supports, capable of deforming without imposing a correlative deformation on the rod
- each of the supports is straight and arranged according to a diameter of the rocket;
- each of the supports is S-shaped;
- each of the inductive sensors is provided with a core secured to the rocket;
- the rod carries a core to influence the inductive sensors.
D'autres caractéristiques ressortent de la description qui suit faite avec référence au dessin annexé sur lequel on peut voir
Figure 1 - une vue schématique en coupe axiale dans un plan vertical d'une fusée de train d'atterrissage équipée du dispositif de contrôle selon l'invention
Figure 2 - une vue simplifiée en coupe axiale dans un plan vertical de la fusée de la figure 1 lorsque l'avion est chargé, les déformations étant volontairement exagérées
Figures 3 à 5 - trois vues en coupe transversale selon la ligne A-A de la figure 1, montrant trois exemples de réalisation du moyen de suspension de la tige, non soumise à déformation, du dispositif de contrôle selon l'invention;
Figures 6 et 7 - deux vues en coupe transversale selon la ligne B-B de la figure 1, montrant deux exemples de réalisation du dispositif de détection différentielle selon l'invention.Other characteristics appear from the following description made with reference to the attached drawing on which one can see
Figure 1 - a schematic view in axial section in a vertical plane of a landing gear rocket equipped with the control device according to the invention
Figure 2 - a simplified view in axial section in a vertical plane of the rocket of Figure 1 when the aircraft is loaded, the deformations being deliberately exaggerated
Figures 3 to 5 - three cross-sectional views along line AA of Figure 1, showing three embodiments of the rod suspension means, not subject to deformation, of the control device according to the invention;
Figures 6 and 7 - two cross-sectional views along line BB of Figure 1, showing two embodiments of the differential detection device according to the invention.
En se reportant au dessin, on peut voir la fusée 1 d'un train d'atterrissage dont les roues sont symbolisées en 2 et 3 et le pilier central en 4. Selon l'invention, on se place à l'intérieur de la fusée, et on suspend dans l'axe de la fusée une tige 5 rigide, destinée à ne pas subir de déformation, et qui symbolise une fibre neutre lorsque la fusée est au repos. Cette tige 5 est suspendue dans l'axe de la fusée 1 au moyen de deux supports 6 et 7 fins, susceptibles de déformations dans le plan radial qui les contient pour absorber éventuellement les contraintes de torsion. Ces supports 6 et 7 peuvent au départ être droits et constituer des diamètres pour la coupe de la fusée (Figure 3), ou bien etre en forme de S plus ou moins accentué (Figures 4 et 5).En cas de déformation de la fusée, ces supports peuvent prendre une forme incurvée comme celle représentée en pointillés sur la figure 3, ou celle de la figure 2. Referring to the drawing, we can see the rocket 1 of a landing gear whose wheels are symbolized in 2 and 3 and the central pillar in 4. According to the invention, we place ourselves inside the rocket , and a rigid rod 5 is suspended in the axis of the rocket, intended not to undergo deformation, and which symbolizes a neutral fiber when the rocket is at rest. This rod 5 is suspended in the axis of the rocket 1 by means of two thin supports 6 and 7, capable of deformation in the radial plane which contains them to possibly absorb the torsional stresses. These supports 6 and 7 can initially be straight and constitute diameters for the cutting of the rocket (Figure 3), or be in the form of S more or less accentuated (Figures 4 and 5). , these supports can take a curved shape like that shown in dotted lines in FIG. 3, or that of FIG. 2.
Selon l'invention, la tige 5 doit être positionnée avec beaucoup de précision. De part et d'autre de la tige 5, dans le plan vertical de la figure 1, on dispose deux capteurs inductifs 8 et 9 de façon à réaliser une détection différentielle. Sur la Figure 2, on a représenté la fusée 1 après chargement de l'avion. La fusée a pris une certaine flèche, qui dans la réalité est au maximum de 0,3mm, ce qui justifie l'exigence de précision sur la position de la tige 5. Comme les capteurs inductifs 8 et 9 sont solidaires en position de la fusée, lorsque celle-ci se déforme sous l'effet de la charge, la partie centrale de la tige 5 se rapproche du capteur 8 et s'éloigne du capteur 9. La détection différentielle permet de mesurer avec précision la déformation de la fusée et, d'après un étalonnage préalable, d'en déduire la charge portée par le train d'atterrissage.Les capteurs 8 et 9 peuvent être des bobines simplement fixées à-l'intérieur de la fusée (figure 1) ou bien des bobines munies de noyaux faisant partie intégrante de la fusée (Figure 6), > ou solidaires de la fusée. According to the invention, the rod 5 must be positioned with great precision. On either side of the rod 5, in the vertical plane of Figure 1, there are two inductive sensors 8 and 9 so as to perform differential detection. In Figure 2, the rocket 1 is shown after loading the aircraft. The rocket took a certain arrow, which in reality is at most 0.3mm, which justifies the requirement of precision on the position of the rod 5. As the inductive sensors 8 and 9 are integral in position of the rocket , when the latter deforms under the effect of the load, the central part of the rod 5 approaches the sensor 8 and moves away from the sensor 9. The differential detection makes it possible to precisely measure the deformation of the rocket and, according to a prior calibration, to deduce the load carried by the landing gear. Sensors 8 and 9 can be coils simply fixed inside the rocket (Figure 1) or coils fitted with cores that are an integral part of the rocket (Figure 6),> or integral with the rocket.
La tige 5 peut être de section droite circulaire, rectangulaire ou carrée. Elle peut influencer les capteurs directement (figure 2) ou par l'intermédiaire d'un noyau 10 qu'elle porte (Figure 7). The rod 5 can be of circular, rectangular or square cross section. It can influence the sensors directly (Figure 2) or through a core 10 that it carries (Figure 7).
Bien entendu, les fils de connexion des capteurs 8 et 9 sont prévus pour ne pas affecter les propriétés mécaniques de la fusée et pour transmettre à l'intérieur de l'avion les signaux électriques utilisables pour la mesure de la charge du train d'atterrissage. Of course, the connection wires of the sensors 8 and 9 are provided so as not to affect the mechanical properties of the rocket and to transmit inside the aircraft the electrical signals which can be used for measuring the load of the landing gear. .
Dans le dispositif selon l'invention, il est important que la tige 5 ne soit pas soumise à des déformations. In the device according to the invention, it is important that the rod 5 is not subjected to deformations.
C'est pourquoi les supports 6 et 7 doivent être fins , et susceptibles de se déformer sans imposer de déformation corrélative à la tige 5.This is why the supports 6 and 7 must be fine, and liable to deform without imposing a correlative deformation on the rod 5.
Le dispositif de contrôle de charge selon l'invention peut assurer une mesure de la charge de maniere statique, c'est-à-dire en toute sécurité, et sans nécessité que l'avion roule. The load control device according to the invention can provide a measurement of the load in a static manner, that is to say in complete safety, and without the need for the aircraft to taxi.
Claims (6)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR8407752A FR2564582A1 (en) | 1984-05-18 | 1984-05-18 | On-board device for monitoring the load of an aeroplane |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR8407752A FR2564582A1 (en) | 1984-05-18 | 1984-05-18 | On-board device for monitoring the load of an aeroplane |
Publications (1)
Publication Number | Publication Date |
---|---|
FR2564582A1 true FR2564582A1 (en) | 1985-11-22 |
Family
ID=9304135
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR8407752A Withdrawn FR2564582A1 (en) | 1984-05-18 | 1984-05-18 | On-board device for monitoring the load of an aeroplane |
Country Status (1)
Country | Link |
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FR (1) | FR2564582A1 (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2626688A1 (en) * | 1988-02-02 | 1989-08-04 | Pfister Gmbh | AIRCRAFT AND METHOD AND APPARATUS FOR ITS PILOTAGE |
EP0482289A2 (en) * | 1990-10-20 | 1992-04-29 | VDO Luftfahrtgeräte Werk GmbH | Mounting of at least one sensor on a landing gear of an aeroplane for measuring the weight and the centre of gravity of the aeroplane |
FR2986322A1 (en) * | 2012-01-30 | 2013-08-02 | Eurocopter France | ON-BOARD DEVICE FOR MEASURING THE MASS AND THE POSITION OF THE CENTER OF GRAVITY OF AN AIRCRAFT |
FR3068004A1 (en) * | 2017-06-26 | 2018-12-28 | Airbus Helicopters | LANDING TRAIN WITH AN ON-LINE LOAD MEASURING DEVICE FOR AN AIRCRAFT AND AIRCRAFT |
EP3640612A1 (en) | 2018-10-16 | 2020-04-22 | Airbus Helicopters | An apparatus for sensing an elastic deformation of a hollow element |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2759356A (en) * | 1945-11-13 | 1956-08-21 | Douglas Aircraft Co Inc | Weight and balance indicator |
US3033032A (en) * | 1958-10-06 | 1962-05-08 | W C Dillon & Company Inc | Dynamometer |
US3203234A (en) * | 1962-06-08 | 1965-08-31 | Cleveland Pneumatic Ind Inc | Aircraft weight and center of gravity determination system |
EP0026446A2 (en) * | 1979-09-28 | 1981-04-08 | Weico Corporation | Strain/deflection sensitive variable reluctance transducer assembly |
FR2471593A1 (en) * | 1979-12-13 | 1981-06-19 | Sacre Louis | Load measuring system for aircraft - includes tubular inductive sensor in each wheel hub and processor providing visual information in cockpit |
-
1984
- 1984-05-18 FR FR8407752A patent/FR2564582A1/en not_active Withdrawn
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2759356A (en) * | 1945-11-13 | 1956-08-21 | Douglas Aircraft Co Inc | Weight and balance indicator |
US3033032A (en) * | 1958-10-06 | 1962-05-08 | W C Dillon & Company Inc | Dynamometer |
US3203234A (en) * | 1962-06-08 | 1965-08-31 | Cleveland Pneumatic Ind Inc | Aircraft weight and center of gravity determination system |
EP0026446A2 (en) * | 1979-09-28 | 1981-04-08 | Weico Corporation | Strain/deflection sensitive variable reluctance transducer assembly |
FR2471593A1 (en) * | 1979-12-13 | 1981-06-19 | Sacre Louis | Load measuring system for aircraft - includes tubular inductive sensor in each wheel hub and processor providing visual information in cockpit |
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2626688A1 (en) * | 1988-02-02 | 1989-08-04 | Pfister Gmbh | AIRCRAFT AND METHOD AND APPARATUS FOR ITS PILOTAGE |
EP0482289A2 (en) * | 1990-10-20 | 1992-04-29 | VDO Luftfahrtgeräte Werk GmbH | Mounting of at least one sensor on a landing gear of an aeroplane for measuring the weight and the centre of gravity of the aeroplane |
EP0482289A3 (en) * | 1990-10-20 | 1992-07-01 | Vdo Adolf Schindling Ag | Mounting of at least one sensor on a landing gear of an aeroplane for measuring the weight and the centre of gravity of the aeroplane |
US5205514A (en) * | 1990-10-20 | 1993-04-27 | Vdo Adolf Schindling Ag | Arrangement of at least one sensor on the landing gear of an aircraft for measuring its weight and position of center of gravity |
FR2986322A1 (en) * | 2012-01-30 | 2013-08-02 | Eurocopter France | ON-BOARD DEVICE FOR MEASURING THE MASS AND THE POSITION OF THE CENTER OF GRAVITY OF AN AIRCRAFT |
US9097573B2 (en) | 2012-01-30 | 2015-08-04 | Airbus Helicopters | On-board device for measuring the weight of an aircraft and the position of its center of gravity |
FR3068004A1 (en) * | 2017-06-26 | 2018-12-28 | Airbus Helicopters | LANDING TRAIN WITH AN ON-LINE LOAD MEASURING DEVICE FOR AN AIRCRAFT AND AIRCRAFT |
EP3421357A1 (en) * | 2017-06-26 | 2019-01-02 | Airbus Helicopters | Landing gear provided with an on-board device for measuring the load of an aircraft, and aircraft |
US10816390B2 (en) | 2017-06-26 | 2020-10-27 | Airbus Helicopters | Aircraft undercarriage having an onboard load-measuring device, and an aircraft |
EP3640612A1 (en) | 2018-10-16 | 2020-04-22 | Airbus Helicopters | An apparatus for sensing an elastic deformation of a hollow element |
US11513028B2 (en) | 2018-10-16 | 2022-11-29 | Airbus Helicopters | Apparatus for sensing an elastic deformation of a hollow element |
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ST | Notification of lapse |