FR2459977A1 - Accelerometer for detecting rough deceleration during aircraft landing - uses spring biassed multi-directional mass making electrical contact with metal ring in response to acceleration or deceleration - Google Patents
Accelerometer for detecting rough deceleration during aircraft landing - uses spring biassed multi-directional mass making electrical contact with metal ring in response to acceleration or deceleration Download PDFInfo
- Publication number
- FR2459977A1 FR2459977A1 FR7916345A FR7916345A FR2459977A1 FR 2459977 A1 FR2459977 A1 FR 2459977A1 FR 7916345 A FR7916345 A FR 7916345A FR 7916345 A FR7916345 A FR 7916345A FR 2459977 A1 FR2459977 A1 FR 2459977A1
- Authority
- FR
- France
- Prior art keywords
- deceleration
- accelerometer
- metal ring
- acceleration
- electrical contact
- 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- Withdrawn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
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P15/00—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration
- G01P15/02—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration by making use of inertia forces using solid seismic masses
- G01P15/08—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration by making use of inertia forces using solid seismic masses with conversion into electric or magnetic values
- G01P15/135—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration by making use of inertia forces using solid seismic masses with conversion into electric or magnetic values by making use of contacts which are actuated by a movable inertial mass
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Details Of Connecting Devices For Male And Female Coupling (AREA)
Abstract
Description
La présente invention concerne les dispositifs sensibles à des variations de vitesse et qui agissent sur un contact électrique lorsqu'une certaine accélération ou décélération prédéterminée est atteinte. The present invention relates to devices sensitive to variations in speed and which act on an electrical contact when a certain predetermined acceleration or deceleration is reached.
Dans les dispositifs connus de ce genre une masse d'inertie, qui peut être une bille, est maintenue en équilibre dans une position déterminée au moyen d'un ressort ou d'un aimant. In known devices of this kind a mass of inertia, which can be a ball, is kept in equilibrium in a determined position by means of a spring or a magnet.
Cet équilibre peut cependant être rompu par une accélération plus ou moins importante qui provoque un deplacement de la masse d'inertie par rapport au boîtier dans lequel elle est incorporée. On utilise ce déplacement pour agir sur l'état d'un contact électrique solidaire du boîtier.This balance can however be upset by a more or less significant acceleration which causes a displacement of the mass of inertia compared to the case in which it is incorporated. This displacement is used to act on the state of an electrical contact secured to the housing.
La présente invention a pour but la réalisation d'un accéléromètre de ce type destiné à détecter les accélérations inhabituelles à bord des aéronefs telles que celles pouvant résulter d'un atterrissage brutal. The object of the present invention is to produce an accelerometer of this type intended to detect unusual accelerations on board aircraft, such as those which may result from a hard landing.
Le dispositif objet de l'invention comprend un boîtier isolant à l'intérieur duquel une masselotte est rendue solidaire d'une coupelle au moyen d'une tige. Cette coupelle est maintenue en appui, par un ressort pression, sur une portée annulaire et plane du boîtier. The device which is the subject of the invention comprises an insulating housing inside which a counterweight is made integral with a cup by means of a rod. This cup is held in abutment, by a pressure spring, on an annular and planar surface of the housing.
L'ensemble coupelle/ressort, conducteur de l'électricité et doré à cet effet, est électriquement relié à une cosse. The cup / spring assembly, electrically conductive and gilded for this purpose, is electrically connected to a terminal.
A proximite et parallèlement à la coupelle, un anneau métallique fixé dans le boîtier est relié à une seconde cosse. Lorsque la masselotte se déplace à la suite d'une accélération ou d'une décélération la coupelle vient en contact avec l'anneau ce qui assure temporairement la liaison électrique entre les deux cosses et permet l'exploitation d'un signal électrique.Near and parallel to the cup, a metal ring fixed in the housing is connected to a second terminal. When the counterweight moves following an acceleration or a deceleration, the cup comes into contact with the ring which temporarily ensures the electrical connection between the two lugs and allows the exploitation of an electrical signal.
Le dessin annexé illustre, à titre d'exemple, un mode de réalisation du dispositif conforme à la présente invention. The appended drawing illustrates, by way of example, an embodiment of the device according to the present invention.
Tel que représenté, il se compose d'un boîtier 1 moulé dans un matériau plastique isolant et qui comprend principalement uen chambre cylindrique lb, deux trous de fixation la, l'a, une portée plane annulaire ic et un chambrage ld dans lequel s'adapte un fond 31. As shown, it consists of a housing 1 molded in an insulating plastic material and which mainly comprises a cylindrical chamber 1b, two fixing holes 1a, 1a, an annular flat surface 1c and a recess ld in which s fits a background 31.
L'ensemble inertiel est constitué par une masselotte cylindrique 21 reliée à une coupelle 23 par une tige rigide 22. The inertial assembly is constituted by a cylindrical counterweight 21 connected to a cup 23 by a rigid rod 22.
Un ressort spiral 24 plaque la coupelle 23 sur la portée ic. A spiral spring 24 presses the cup 23 on the bearing ic.
Sa force d'armage peut être réglée en vissant plus ou moins le bouchon en laiton 33 (sur lequel est rivée une cosse 25) dans le fond 31 en matériau isolant.Its winding force can be adjusted by screwing more or less the brass plug 33 (on which a terminal 25 is riveted) in the bottom 31 of insulating material.
Un anneau métallique 27 pourvu daine cosse 27a est disposée parallélement à quelques millimètres de la coupelle 23. L'ensemble cosse 25, bouchon 33, ressort 24 passant au travers de l'anneau 27, et la coupelle 23, peut être doré pour faciliter le passage de faibles courants, ainsi que l'ensemble 27, 27a.A metal ring 27 provided with a thimble 27a is disposed parallel to a few millimeters from the cup 23. The thimble assembly 25, plug 33, spring 24 passing through the ring 27, and the cup 23, can be gilded to facilitate the passage of weak currents, as well as the assembly 27, 27a.
A titre d'exemple, pour la détection d'une accélération de 10 g dans l'axe de la tige 22 (dans la direction de la flèche
F) et d'une accélération de l'ordre de 8 g dans toutes les directions du plan XY perpendiculaire à cet axe au niveau de la portée lc, le ressort doit avoir une force de 50 grammes pour une coupelle de 16 mm de diamètre et une masselotte en dural de 4 à 5 grammes dont le centre de gravité se situe à environ 13 mm audessus du plan XY.For example, for the detection of an acceleration of 10 g in the axis of the rod 22 (in the direction of the arrow
F) and an acceleration of the order of 8 g in all directions of the XY plane perpendicular to this axis at the level of the span lc, the spring must have a force of 50 grams for a cup with a diameter of 16 mm and a dural weight of 4 to 5 grams, the center of gravity of which is approximately 13 mm above the XY plane.
Le dispositif objet de l'invention peut être utilisé à bord des aéronefs pour déceler les décélérations trop brutales susceptibles d'endommager le matériel au cours des atterrissages. The device which is the subject of the invention can be used on board aircraft to detect excessively sudden decelerations liable to damage the equipment during landings.
Claims (2)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR7916345A FR2459977A1 (en) | 1979-06-22 | 1979-06-22 | Accelerometer for detecting rough deceleration during aircraft landing - uses spring biassed multi-directional mass making electrical contact with metal ring in response to acceleration or deceleration |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR7916345A FR2459977A1 (en) | 1979-06-22 | 1979-06-22 | Accelerometer for detecting rough deceleration during aircraft landing - uses spring biassed multi-directional mass making electrical contact with metal ring in response to acceleration or deceleration |
Publications (1)
Publication Number | Publication Date |
---|---|
FR2459977A1 true FR2459977A1 (en) | 1981-01-16 |
Family
ID=9227082
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR7916345A Withdrawn FR2459977A1 (en) | 1979-06-22 | 1979-06-22 | Accelerometer for detecting rough deceleration during aircraft landing - uses spring biassed multi-directional mass making electrical contact with metal ring in response to acceleration or deceleration |
Country Status (1)
Country | Link |
---|---|
FR (1) | FR2459977A1 (en) |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2596427A (en) * | 1951-10-26 | 1952-05-13 | American Seating Co | Inertia-operated switch |
US2768256A (en) * | 1955-01-06 | 1956-10-23 | American Seating Co | Inertia-operated electric switch |
FR2161233A5 (en) * | 1971-11-18 | 1973-07-06 | Dav | |
US3898400A (en) * | 1972-11-29 | 1975-08-05 | Takata Kojyo Co | Pendulum type inertia switch |
-
1979
- 1979-06-22 FR FR7916345A patent/FR2459977A1/en not_active Withdrawn
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2596427A (en) * | 1951-10-26 | 1952-05-13 | American Seating Co | Inertia-operated switch |
US2768256A (en) * | 1955-01-06 | 1956-10-23 | American Seating Co | Inertia-operated electric switch |
FR2161233A5 (en) * | 1971-11-18 | 1973-07-06 | Dav | |
US3898400A (en) * | 1972-11-29 | 1975-08-05 | Takata Kojyo Co | Pendulum type inertia switch |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
ST | Notification of lapse |