WO2000060363A1 - Girouette destinee a s'orienter dans l'axe d'un ecoulement d'air ambiant - Google Patents
Girouette destinee a s'orienter dans l'axe d'un ecoulement d'air ambiant Download PDFInfo
- Publication number
- WO2000060363A1 WO2000060363A1 PCT/FR2000/000825 FR0000825W WO0060363A1 WO 2000060363 A1 WO2000060363 A1 WO 2000060363A1 FR 0000825 W FR0000825 W FR 0000825W WO 0060363 A1 WO0060363 A1 WO 0060363A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- vane
- oriented
- ambient air
- air flow
- pressure
- Prior art date
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P21/00—Testing or calibrating of apparatus or devices covered by the preceding groups
- G01P21/02—Testing or calibrating of apparatus or devices covered by the preceding groups of speedometers
- G01P21/025—Testing or calibrating of apparatus or devices covered by the preceding groups of speedometers for measuring speed of fluids; for measuring speed of bodies relative to fluids
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P13/00—Indicating or recording presence, absence, or direction, of movement
- G01P13/02—Indicating direction only, e.g. by weather vane
- G01P13/025—Indicating direction only, e.g. by weather vane indicating air data, i.e. flight variables of an aircraft, e.g. angle of attack, side slip, shear, yaw
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P5/00—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft
- G01P5/14—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid
- G01P5/16—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid using Pitot tubes, e.g. Machmeter
- G01P5/165—Arrangements or constructions of Pitot tubes
Definitions
- the invention relates to a wind vane intended to orient itself in the axis of an ambient air flow.
- Such a wind vane is advantageously used in an aircraft probe intended to measure aerodynamic parameters of the ambient air flow of the aircraft.
- the piloting of any aircraft implies knowing the relative speed of the aircraft with respect to the ambient air, that is to say the relative wind. This speed is determined using the static pressure po, the total pressure pt and the angle of incidence ⁇ sensors. ⁇ provides the direction of the speed vector in a reference system linked to the aircraft and pt - po provides the modulus of this speed vector.
- the three aerodynamic parameters therefore make it possible to determine the speed vector of an airplane and, incidentally, of a tilting rotor aircraft said to be convertible.
- a wind vane described in French patent FR 2 665 539 shows the advantage for the probe to orient itself in the axis of the ambient air flow in order to facilitate the measurement of the angle of incidence.
- this patent describes the use of a mechanical control to cancel the aerodynamic incidence of the vane. This control is especially useful at low ambient air flow speeds because, the lower the speed, the lower the aerodynamic forces of the air on the vane and are not sufficient to overcome the mechanical friction forces to orient correctly the wind vane in the axis of the ambient air flow.
- the use of servo-control based on the cancellation of the aerodynamic incidence of the wind vane nevertheless presents a drawback.
- the inevitable imperfections in the realization of the vane make that an angular gap exists between the orientation of the vane due to aerodynamic forces at high flow speeds and the orientation of the vane due to the 'control at low flow velocities.
- the control system can attempt to modify the orientation of the vane without succeeding because of the importance of aerodynamic forces which leads to unnecessary consumption of electrical power on the part of the control system.
- the object of the invention is to overcome these drawbacks by proposing a device which improves the consistency of the orientation of the wind vane whatever the speed of the flow of ambient air.
- the invention relates to a wind vane device intended to orient itself in the axis of an ambient air flow and provided with differential pressure measurement means representative of the aerodynamic incidence of the vane , characterized in that the differential pressure tap is balanced when the vane is oriented naturally in the axis of the flow.
- An advantage linked to the invention is to limit the cost of producing the weather vane by avoiding tightening the tolerances of position shape and dimensions in defining the profile of the weather vane.
- Another advantage linked to the invention is to avoid introducing corrections in the servo control parameters, which would hinder the interchangeability of the movable vane of the wind vane alone, without the servo means.
- FIG. 1 shows a weather vane according to the invention
- FIG. 2 shows the inside of a palette of the weather vane.
- the wind vane 1 shown in Figure 1 is movable in rotation about an axis 2. It comprises for example a shaft 3 of axis 2 which penetrates inside the skin 4 of an aircraft.
- the shaft 3 is movable in rotation relative to the aircraft for example by means of a rolling bearing 5.
- the shaft 3 is driven in rotation by means of a motor 6 intended to orient the wind vane 1 in a precise angular position around the axis 2.
- the shaft 3 is integral with means 7 for measuring its angular position. These means 7 comprise for example an optical encoder.
- the angular position of the wind vane 1, available at the output of the means 7, defines the angle of incidence ⁇ of the aircraft.
- the shaft 3 is also integral with a pneumatic seal 8 enabling the pneumatic information taken by the vane 1 to be transmitted to processing means 9.
- the wind vane 1 may include means for taking total pressure pt comprising a tube 10 open at one of its ends 11.
- the tube 10 is substantially oriented in the axis of the ambient air flow 12 when the vane is oriented in the axis of the flow 12.
- the vane 1 may also include means for taking static pressure po located on the side of the tube 10. These means are not shown in FIG. 1.
- the wind vane 1 comprises a pallet 15 having for example the shape of a delta half-wing.
- the pallet 15 is symmetrical with respect to the plane of FIG. 1.
- the pallet has a leading edge 16.
- the pallet 15 comprises differential pressure measurement means. These means comprise on at least one face of the pallet 15, for example the lower surface, two orifices 11 and 12 situated respectively at a distance e1 and e2 from the leading edge 16.
- the orifices 11 and 12 both communicate with a chamber 20 which is better defined from FIG. 2.
- FIG. 2 shows the pallet 15 in section along a plane perpendicular to the plane of FIG. 1 and to the leading edge 16.
- the profile of the pallet 15 shown in FIG. 2 is symmetrical with respect to a plane 21 perpendicular to FIG. 2.
- the profile is for example that of an airplane wing.
- the two orifices 11 and 12 communicate with the chamber 20 located inside the pallet 15.
- the two orifices E1 and E2 communicate with a chamber 22 also located inside the pallet 15.
- the chamber 20 communicates via a tubing 23 with the pneumatic seal 8 shown in FIG. 1.
- the chamber 22 communicates via a tubular 24 with the pneumatic seal 8.
- the pneumatic seal delivers the pressure from chamber 20 and that of chamber 22 to treatment means 9.
- the treatment means 9 compare these pressures and generate a control signal c of motor 6 so as to orient the pallet 15 so such that the pressure in the chamber 20 is equal to the pressure in the chamber 22.
- the processing means 9 may comprise a flow meter detecting a deviation from a zero flow between the two chambers 20 and 22.
- PI1 + PI2 PI • PU is the air pressure at the orifice 11 and PI2 is the air pressure at the orifice 12.
- the pressure PU is greater than the pressure PI2. This pressure difference is due to the difference between the distances e1 and e2. The closer the orifice, in this case 11, to the leading edge 16, the stronger the pressure PU therein.
- the wind vane 1 can be placed in a wind tunnel in a flow 12 at high speed so that the pallet 15 is oriented naturally in the axis of the flow without the processing means 9 controlling the motor 6. If there is a difference in pressure between the chambers 20 and 22, a dimension of one of the orifices is modified, for example 11 or 12 so as to modify the pressure of one of the chambers to substantially cancel the difference in pressure between the two chambers 20 and 22.
- the other chamber may have only one orifice.
- the two chambers 20 and 22 both have orifices symmetrical with respect to the plane 21.
- the orifices 11, 12, E1 and E2 are unique. However, it can be provided that one (or more) of these orifices is (are) multiple (s), this in order to ensure a minimum air flow in the pipes 23 and 24 so that the flow meter, located in the means of treatment 9, can function properly without the dimensions of the orifice considered being too large to the point of modifying the flow 12 in its vicinity. It is also conceivable that the different orifices have different dimensions. For example, the surface of the orifice 11 may be less than that of the orifice 12.
- the pressure PI prevailing inside the chamber will then be of the form: al.PIl + a2.
- PI2 2 ai and a2 are coefficients depending on the surfaces of the orifices 11 and 12.
- the invention can just as easily be implemented.
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US09/926,231 US6698281B1 (en) | 1999-04-02 | 2000-03-31 | Vane designed to get oriented in the ambient air flow axis |
CA002369059A CA2369059A1 (fr) | 1999-04-02 | 2000-03-31 | Girouette destinee a s'orienter dans l'axe d'un ecoulement d'air ambiant |
EP00915273A EP1166127A1 (fr) | 1999-04-02 | 2000-03-31 | Girouette destinee a s'orienter dans l'axe d'un ecoulement d'air ambiant |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9904183A FR2791773B1 (fr) | 1999-04-02 | 1999-04-02 | Girouette destinee a s'orienter dans l'axe d'un ecoulement d'air ambiant |
FR99/04183 | 1999-04-02 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2000060363A1 true WO2000060363A1 (fr) | 2000-10-12 |
Family
ID=9543986
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2000/000825 WO2000060363A1 (fr) | 1999-04-02 | 2000-03-31 | Girouette destinee a s'orienter dans l'axe d'un ecoulement d'air ambiant |
Country Status (5)
Country | Link |
---|---|
US (1) | US6698281B1 (fr) |
EP (1) | EP1166127A1 (fr) |
CA (1) | CA2369059A1 (fr) |
FR (1) | FR2791773B1 (fr) |
WO (1) | WO2000060363A1 (fr) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1493037B1 (fr) * | 2002-04-10 | 2013-03-27 | Honeywell International Inc. | Detecteur de mesure d'un angle au vent |
CN106885922A (zh) * | 2017-01-23 | 2017-06-23 | 湘电风能有限公司 | 一种用于风力发电机组的风向标校准装置和方法 |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20050044186A1 (en) * | 2003-06-13 | 2005-02-24 | Petrisor Gregory C. | Remote interface optical network |
EP1938484A2 (fr) * | 2005-09-19 | 2008-07-02 | Lumexis, Inc. | Systeme de projection de films en cours de vol par fibre jusqu'aux sieges |
WO2008033870A2 (fr) * | 2006-09-11 | 2008-03-20 | Lumexis Corporation | Système de distribution par fibres de type fibre jusqu'au siège |
US8255161B2 (en) * | 2008-10-03 | 2012-08-28 | Honeywell International Inc. | System and method of auto-calibration of inertial sensors |
US8364334B2 (en) * | 2008-10-30 | 2013-01-29 | Honeywell International Inc. | System and method for navigating an autonomous vehicle using laser detection and ranging |
WO2011017233A1 (fr) | 2009-08-06 | 2011-02-10 | Lumexis Corporation | Système de divertissement en vol par fibre jusquaux sièges à mise en réseau série |
US20110162015A1 (en) * | 2009-10-05 | 2011-06-30 | Lumexis Corp | Inflight communication system |
WO2011020071A1 (fr) * | 2009-08-14 | 2011-02-17 | Lumexis Corp. | Dispositif de connexion d'unité d'affichage vidéo pour un système fibre à l'écran de divertissement à bord |
WO2011022708A1 (fr) | 2009-08-20 | 2011-02-24 | Lumexis Corp. | Configuration de réseau de système de divertissement en vol à fibres optiques à mise en réseau série |
US20120260842A1 (en) * | 2011-04-14 | 2012-10-18 | Douglas Moreland King | Vehicle flag |
FR3002320B1 (fr) * | 2013-02-20 | 2016-05-20 | Airbus Operations Sas | Sonde de mesure angulaire a bord d'un aeronef et aeronef mettant en oeuvre au moins une telle sonde |
US10670473B2 (en) * | 2017-07-25 | 2020-06-02 | Rolls-Royce North American Technologies, Inc. | Sensor with integral vortex tube for warming |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2105080A1 (fr) * | 1970-09-23 | 1972-04-28 | Thomson Csf | |
FR2665539A1 (fr) * | 1990-08-03 | 1992-02-07 | Sextant Avionique | Sonde d'aeronef pour la mesure des parametres aerodynamiques de l'ecoulement ambiant. |
WO1993003326A1 (fr) * | 1991-08-08 | 1993-02-18 | Rosemount Inc. | Capteur d'angle d'attaque, utilisant un rapport inverse de differences de pression |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2584822B1 (fr) | 1985-07-09 | 1988-06-17 | Thomson Csf | Dispositif de mesure du rapport de deux capacites de faibles valeurs |
FR2634885B1 (fr) | 1988-07-26 | 1990-10-05 | Thomson Csf | Capteur capacitif d'angle de torsion et appareil de mesure de couple muni d'un tel capteur |
FR2645259B1 (fr) | 1989-04-04 | 1994-02-11 | Thomson Csf | Capteur capacitif de deplacements et capteur d'angle de torsion comportant au moins un tel capteur capacitif |
FR2694634B1 (fr) * | 1992-08-04 | 1994-09-30 | Sextant Avionique | Sonde d'incidence. |
FR2768122B1 (fr) | 1997-09-09 | 1999-11-19 | Sextant Avionique | Dispositif optique de detection de conditions givrantes sur aeronef |
US6378361B1 (en) * | 1999-07-16 | 2002-04-30 | Vertical Wind Tunnel Corporation | Method and apparatus for creating a wind tunnel by redirecting an air flow ninety degrees |
-
1999
- 1999-04-02 FR FR9904183A patent/FR2791773B1/fr not_active Expired - Lifetime
-
2000
- 2000-03-31 CA CA002369059A patent/CA2369059A1/fr not_active Abandoned
- 2000-03-31 US US09/926,231 patent/US6698281B1/en not_active Expired - Fee Related
- 2000-03-31 WO PCT/FR2000/000825 patent/WO2000060363A1/fr not_active Application Discontinuation
- 2000-03-31 EP EP00915273A patent/EP1166127A1/fr not_active Withdrawn
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2105080A1 (fr) * | 1970-09-23 | 1972-04-28 | Thomson Csf | |
FR2665539A1 (fr) * | 1990-08-03 | 1992-02-07 | Sextant Avionique | Sonde d'aeronef pour la mesure des parametres aerodynamiques de l'ecoulement ambiant. |
WO1993003326A1 (fr) * | 1991-08-08 | 1993-02-18 | Rosemount Inc. | Capteur d'angle d'attaque, utilisant un rapport inverse de differences de pression |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1493037B1 (fr) * | 2002-04-10 | 2013-03-27 | Honeywell International Inc. | Detecteur de mesure d'un angle au vent |
CN106885922A (zh) * | 2017-01-23 | 2017-06-23 | 湘电风能有限公司 | 一种用于风力发电机组的风向标校准装置和方法 |
CN106885922B (zh) * | 2017-01-23 | 2019-07-23 | 湘电风能有限公司 | 一种用于风力发电机组的风向标校准装置和方法 |
Also Published As
Publication number | Publication date |
---|---|
FR2791773B1 (fr) | 2001-06-15 |
FR2791773A1 (fr) | 2000-10-06 |
CA2369059A1 (fr) | 2000-10-12 |
EP1166127A1 (fr) | 2002-01-02 |
US6698281B1 (en) | 2004-03-02 |
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