Classifications

• • 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 device for measuring the total pressure of a flow.
• the invention also relates to a method of implementing a device according to the invention.
• the piloting of any aircraft requires knowing its relative speed with respect to the air, that is to say to the relative wind. This speed is determined using sensors of the static pressure Ps, the total pressure Pt, the angle of incidence ⁇ and the skid angle ⁇ .
• ⁇ and ⁇ provide the direction of the velocity vector in a reference system, or reference system, linked to the aircraft and Pt - Ps provides the modulus of this velocity vector.
• the four aerodynamic parameters thus make it possible to determine the speed vector of an aircraft and, incidentally, of a so-called convertible rocker aircraft.
• the measurement of the total pressure Pt is usually done using a pitot tube. It is an open tube at one end and obstructed at the other. The open end of the tube substantially faces the flow.
• the airflow can convey solid or liquid particles that can enter the pitot tube and accumulate in the tube at the obstructed end.
• a purge hole through which any particles can evacuate.
• a total pressure probe has been used with a fluid stopping point. More specifically, this probe takes at least two air streams in an air flow and brings them into contact with one another so as to slow them down. The pressure in the zone where the air is slowed down is measured and this measured pressure gives the total pressure of the flow.
• a probe is described in patent application No. FR 2 823 846.
• the two types of probe are not susceptible to the same risks of clogging.
• the pitot tube fears small particles from clogging its bleed hole.
• the fluid stopping probe fears larger particles, such as for example a bird, from obstructing the area where the air streams are taken.
• An object of the invention is to overcome this problem by proposing to combine the two types of probe.
• Another object of the invention is to propose a redundant probe where the total pressure measurement is made of two different principles. This limits any common mode faults that would impair redundant probes made according to the same principle.
• the subject of the invention is a device for measuring the total pressure of a flow, comprising a pitot tube, characterized in that it furthermore comprises means for taking total pressure at a breakpoint. fluid and means for comparing pressures measured by the pitot tube and the fluid-stop total pressure tap means, the pitot tube, and the fluid-stop total pressure tap means being integral and taking air streams from the flow along the same axis.
• the invention also relates to a method for measuring the total pressure of a flow using the device described above, characterized in that it consists of:
• FIG. 1 represents a device for measuring the total pressure of a flow comprising means for taking total pressure with a fluid stopping point
• FIG. 2 shows a device for measuring the total pressure of a flow comprising both a Pitot tube and a total pressure point with fluid stopping point, the device being fixed relative to the skin of an aircraft
• Figure 3 shows the device of Figure 2 secured to a pallet for orientation in the axis of the flow
• FIG. 4 represents steps of a method implementing the device of the invention.
• the same elements will bear the same references in the different figures.
• FIG. 1 represents a total pressure setting device whose position is fixed relative to the skin 1 of an aircraft on which it is arranged.
• the device is fixed on a mast 2 making it integral with the skin 1.
• the device comprises a hollow body 3 comprising a channel 4.
• the device is located in an air flow whose direction is represented by the arrow 5.
• the channel 4 has an upstream end 6 opening substantially perpendicular to the direction 5 of the flow.
• the channel 4 has a substantially tubular shape about an axis 7.
• the channel 4 is located between an outer cylindrical wall 8 and an inner cylindrical wall 9.
• the two walls extend along the axis 7.
• the inner cylindrical wall 9 ends with a rounded end 10 to separate the air streams entering the channel 4.
• the embodiment shown in Figure 1 advantageously has a symmetry of revolution about the axis 7 oriented in the direction 5 of the air flow.
• the circulation of the air streams flowing in the channel 4 is represented by arrows 11.
• the various air streams flowing in the channel 4 are brought into contact with each other to form a fluid stopping point in an area 12 of the hollow body 3 before escaping from the hollow body 3 by at least one downstream orifice.
• the channel 4 closes around the zone 12 where the different air streams flowing in the channel 4 are brought into contact so as to slow each other down.
• the hollow body 3 has two downstream orifices 15 and 16.
• the orifice 15 is situated in the extension of the outer wall 8 and allows the air streams to escape from the zone 12 directly into the chamber. flow in the direction 5 along the axis 7.
• the orifice 16 is located in the extension of the inner wall 9 and allows the air streams to escape from the zone 12 in the direction opposite to the direction 5 of the flow.
• the air streams discharged through the orifice 16 open into an internal channel 17 located partly in the mat 2 and rejecting the air streams therein in the flow along an axis 18 parallel to the axis 7.
• An orifice 20 of a tube 21 is located in the zone 12 and makes it possible to take a pressure tap in the zone 12.
• the hollow body 3 is integral with the mast 2 inside which the tube 21 extends.
• the pressure air prevailing in zone 12 is representative of the total pressure Pt prevailing in the flow.
• the tube 21 is connected at its second end to pressure measuring means such as for example a pressure sensor.
• This pressure sensor may be located inside the aircraft, in which case the tube 21 extends from the inside of the hollow body 3 to the inside of the aircraft while passing inside the aircraft. mast 2.
• the channel 4 formed between the walls 8 and 9 has been shown in a fixed position with respect to the skin 1 of the aircraft. It is also possible to fix the channel 4 on a moving pallet in order to improve the alignment of the channel 4 with respect to the axis 7 of the flow when the aircraft modifies its direction with respect to the axis 7 of the 'flow.
• FIG. 2 shows a device for measuring the total pressure of a flow comprising both a Pitot tube and a fluid-stopping total pressure setting means. More specifically, we find the various elements of the device of Figure 1 to which is added the Pitot tube 25 having an opening 26 for withdrawing air in the flow. The opening 26 is located inside the channel 4.
• the Pitot tube 25 advantageously comprises a bleed hole, not shown in Figure 2 and for discharging from the Pitot tube 25 any particles entering it, as for example drops of water present in the flow.
• the purge hole opens at the bottom of the pitot tube and opens for example into the inner channel 17.
• the opening 26 of the pitot tube 25 is located downstream of the upstream end 6 forming an opening, also bearing the mark 6.
• the opening 6 of the total pressure tap means with a fluid stop point allows the sampling the air streams from the flow.
• the upstream and downstream qualifiers are defined according to the direction of flow.
• the opening 26 of the Pitot tube 25 is located on the inner cylindrical wall 9 at the rounded end 10.
• the air flow inside the Pitot tube 25 is much lower than that flowing in the channel 4 in the direction of the zone 12. Consequently, the presence of the Pitot tube 25 inside the channel 4 does not disturb the operation of the total pressure point with a fluid stopping point.
• the fact that the opening 26 is located downstream of the opening 6 makes it possible to guide the flow upstream of the Pitot tube 25.
• the opening 26 of the Pitot tube 25 is substantially circular and centered on the axis 7 of the channel 4, in order to ensure a good symmetry of the device and more principally a symmetry in the flow of the air streams at the same time. This symmetry is important to ensure a good position of the zone 12.
• An orifice 27 of a tube 28 is located at the bottom of the Pitot tube 25 and makes it possible to take a pressure tap designed to measure the pressure at the bottom of the Pitot tube 25. This pressure corresponds to the total pressure of the flow. .
• the tube 28 extends inside the mat 2.
• the pressure taps of the zone 12 and the pitot tube 25 give two redundant information on the total pressure of the flow. These two pieces of information are obtained by different principles, one by a pitot tube and the other by a fluid stopping point, and are therefore not sensitive to the same risks of errors.
• the device further comprises means for comparing pressures measured by the pitot tube 25 and the total pressure tap means with a fluid stopping point.
• Each of the tubes 21 and 28 includes a second end, respectively 30 and 31 located inside the aircraft. In a simple manner, it is possible to measure each of the pressures in the tubes 21 and 28 by means of two pressure sensors each disposed at one of the ends 30 and 31. The comparison means compare the values obtained by each of the pressure sensors.
• the comparison means comprise a differential pressure sensor or a flowmeter 32 making it possible to dispense with one of the two pressure sensors.
• the device comprises only one absolute pressure sensor 33 measuring the pressure at the total pressure setting point with fluid stopping point.
• the fluid stop point makes it possible to tolerate particles penetrating into the channel 4 of larger dimensions than for the Pitot tube 25 without drift measuring the total pressure. The risk of clogging is therefore lower for the means of total pressure tap at fluid stopping point.
• FIG. 2 describes a device comprising the pitot tube 25 and the fluid stop point total pressure setting means having a fixed position relative to the skin 1 of an aircraft. It is also possible, in order to limit the effect of modifying the local incidence of the flow on the pressure measurements, to make the Pitot tube 25 and the total pressure setting means with a fluid stopping point integral. means for orienting in the axis of the flow.
• FIG. 3 represents another embodiment of the invention in which the hollow body 3 has a position that is movable relative to the skin 1 of an aircraft.
• the channel 4 and the zone 12 forming the fluid-stopping total pressure setting means as well as the pitot tube 25.
• the hollow body 3 is fixed on a pallet 35 movable about an axis 36
• the pallet 35 is intended to orient in the bed of the flow as a function of the local incidence of the flow in the vicinity of the device.
• the pallet 35 is integral with a shaft 37 substantially perpendicular to the skin 1 of the aircraft.
• a bearing 38 for example rolling, makes it possible to ensure easy rotation of the shaft 37 relative to the skin of the aircraft while ensuring precise positioning according to the degrees of freedom of the bearing other than the rotation around the plane.
• axis 36 for example rolling
• the device comprises heating means allowing it to operate at high altitude, in an environment where frost may form on the walls of the device and more particularly in the channel 4 or in the Pitot tube 25. example a heating electric resistance drowned in solid portions of the probe surrounding the channel 4 and the pitot tube 25.
• the heating means may be implemented both for a device having a fixed position that a position movable relative to the skin of the aircraft. In the case of a device whose position is mobile, resistance supply wires pass through the rotary joint.
• FIG. 4 represents steps of a method implementing the device of the invention.
• a first step 40 consists of comparing the pressures measured by the two pressure taps, that associated with the pitot tube and that associated with the fluid stop point. In other words, the pressures measured at the two tubes 21 and 28 are compared. The comparison can be made directly by the flowmeter or differential pressure sensor 32. In the case of a flowmeter, the pressure difference is a function of the density air and its temperature. These two parameters are determined by means of other probes external to the device.
• a second step 41 consists in comparing the difference obtained in step 40 with a given deviation E which may be a function of the flight phase in which the aircraft is located, takeoff, landing or cruising.
• the value of the difference E can be a function of the implementation or not of a reduced vertical separation between aircraft, well known in the English literature as the RVSM for "Reduce Vertical Separation Minimum”. If the difference is smaller than the given difference E, it is considered, in a step 42, that the two measured pressures are correct. If, on the contrary, the difference between the two measured pressures is greater than the given distance E, an alert is generated in a step 43, for the attention of the pilot of the aircraft, stating that only the highest pressure has a good probability of being correct.
• the lowest pressure measurement is declared invalid and the highest pressure measurement is kept. Indeed in a total pressure measuring device, the most likely cause of failure is the plugging of either channel 4 leading to zone 12 or the Pitot tube 25. Such clogging causes a pressure measurement close to the static pressure of the flow and therefore less than the total pressure. Declaring a measure invalid allows you to generate an alert to warn operators, such as the pilot and the maintenance personnel of the aircraft.
• the two pressure measurements are declared invalid. This case can be detected by a sudden variation of the measured pressures. Such a variation is not likely under normal flight conditions and will therefore be interpreted as a defect of the entire device.

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• Engineering & Computer Science (AREA)
• Aviation & Aerospace Engineering (AREA)
• Physics & Mathematics (AREA)
• General Physics & Mathematics (AREA)
• Measuring Fluid Pressure (AREA)
• Measuring Volume Flow (AREA)

Applications Claiming Priority (2)

Publications (1)

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Family Applications (1)

Country Status (5)

Cited By (1)

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• 2006
  • 2006-11-17 FR FR0610076A patent/FR2908882B1/fr active Active
• 2007
  • 2007-11-07 EP EP07822290A patent/EP2113084A2/de not_active Withdrawn
  • 2007-11-07 WO PCT/EP2007/061976 patent/WO2008058872A2/fr not_active Ceased
  • 2007-11-07 US US12/515,159 patent/US8100022B2/en active Active
  • 2007-11-07 CN CN2007800465098A patent/CN101558315B/zh not_active Expired - Fee Related

Non-Patent Citations (1)

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