• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    - Method and device for estimating the Mach number of an aircraft. - the device comprises a measurement unit (2) for measuring a first static pressure of the ambient air at a first measurement zone (20) of the aircraft (100), a measurement unit (3) for measuring a second pressure of the ambient air, by means of at least one static pressure probe, at a second measurement zone (21) of the aircraft (100), the second pressure having a value less than the first static pressure, a calculation unit for estimating a Mach number using these two measured pressures and a data transmission unit configured to transmit the estimated Mach number to a user system.
    公开号:FR3024238A1
    申请号:FR1457105
    申请日:2014-07-23
    公开日:2016-01-29
    发明作者:Maxime Semat；Martin Delporte
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a method and a device for estimating the Mach number of an aircraft. It is known that the Mach number of an aircraft is defined as the ratio between the speed of the aircraft and the speed of sound in the flight conditions of the aircraft. The laws of thermodynamics make it possible to define a relation between the Mach number of the air flow, the total pressure Pt and the static pressure Ps, which is expressed as follows: In this equation, y represents the adiabatic index, which is equal to 1.4 for the air. Thanks to this equation, the measurements of the static pressure Ps and of the total pressure Pt are sufficient to calculate the number of Mach M. The static pressure Ps corresponds to the atmospheric pressure which depends on the altitude of the aircraft and the ambient temperature. It can be measured using a probe placed on the aircraft.
    [0002] In addition, the total pressure Pt is the sum of the static pressure and the impact pressure due to the speed of the aircraft. The total pressure Pt is measured by pitot probes. In the event of errors from pitot probes, the Mach number calculated using the above equation may therefore be erroneous.
    [0003] Patent CA2783222 discloses a method of measuring the Mach number by means of measurements of two static pressures at the motor. These measurements make it possible to estimate static pressure Ps and estimate total pressure Pt. By introducing these estimated pressure values into the aforementioned equation, an estimate of Mach number M is obtained. Static pressure sensor that makes such an estimate of total pressure is not available on all types of aircraft and on all types of engines. The present invention relates to a method for estimating the Mach number of an aircraft, making it possible to estimate the Mach number without using a total pressure value, in order to be able in particular to provide the pilot with information from the aircraft. Mach number even in the absence of a reliable total pressure value available on the aircraft. For this purpose, said process for estimating the Mach number comprises, according to the invention, the following successive steps automatically consisting of: A) measuring a first static pressure Ps of the ambient air at the level of a first measurement zone located on the aircraft; B) measuring a second pressure P of the ambient air, by means of at least one static pressure probe, at a second measurement zone situated on the aircraft, said second pressure P having a value less than said first static pressure Ps; C) estimating a Mach number of the aircraft, using the following expression: k4 + 4k2 - k2 M 2 15 the parameter k satisfying the expression k = Z (1-ks.) In which Z is a parameter dependent on the position of the second measurement zone on the aircraft; and D) transmitting the estimated Mach number to a user system. Thanks to the invention, it is possible to estimate the Mach number using only two static pressure measurements. Thus, it is not necessary to use a total pressure value (measured by pitot probes) and one is therefore able to calculate an estimated Mach number, even in the absence of a total pressure value. reliable available (no value or erroneous value) on the aircraft.
    [0004] According to various embodiments of the invention, which can be taken together or separately: the second measurement zone is located on a fuselage of the aircraft, the parameter Z satisfying the following relationship Z = 2 in which Cpo is a Cpo * y constant pressure coefficient and y the adiabatic index of air; The second measurement zone is located in the nacelle of an engine of the aircraft, the parameter Z satisfying the following relationship Z = (aN1 + b) in which a and b are empirically determined constants and N1 represents the rotational speed of the engine blower; Step A comprises sub-steps consisting of: Aa) measuring a first intermediate static pressure Ps' and a second intermediate static pressure Ps "in said first measurement zone, respectively, at a first measurement point intermediate and a second intermediate measurement point; and Ab) estimating the first static pressure Ps by averaging the first and second intermediate static pressures Ps' and Ps "measured in the previous step Aa); the first intermediate measurement point and the second intermediate measurement point are situated on a fuselage of the aircraft, on either side of a longitudinal axis of the aircraft; The present invention also relates to a device for estimating the Mach number of an aircraft. According to the invention, said estimation device comprises: a first measurement unit configured to measure a first static pressure Ps of the ambient air at a first measurement zone of the aircraft; a second measurement unit configured to measure a second pressure P of the ambient air, by means of at least one static pressure probe, at a second measurement zone of the aircraft, the second pressure P 25 having a value lower than the first static pressure Ps; a calculation unit configured to estimate a Mach number of the aircraft, using the following expression: + 4k2-k2 2 3024238 4 the parameter k satisfying the expression k = Z (1 - pis) in which Z is a parameter dependent on the position of the second measurement zone on the aircraft; and a data transmission unit configured to transmit the estimated Mach number to a user system. The invention also relates to an aircraft, in particular a transport aircraft, which comprises a device such as that described above. In a particular embodiment, the first measurement unit comprises first and second measurement probes configured to measure a first intermediate static pressure Ps' and a second intermediate static pressure Ps ", said first measurement unit further comprising a computer configured to determine the first static pressure Ps by averaging the first and second intermediate static pressures Ps' and Ps ".
    [0005] Advantageously, the first and the second measurement probes are positioned on a fuselage of the aircraft, on either side of a longitudinal axis of the aircraft. FIG. 1 is a schematic view showing a device for estimating the Mach number of an aircraft.
    [0006] FIG. 2 is a diagrammatic view showing an aircraft comprising the device of FIG. 1. FIG. 3 is a schematic view showing the steps for calculating a calculation unit of the device of FIG. 1. An estimation device 1 the Mach number M of an aircraft, in particular of a transport plane, is shown diagrammatically in FIG. 1. Such an estimating device 1 (denoted hereinafter device 1) comprises, according to the invention, a first unit measuring circuit 2 configured to measure a first static pressure Ps of the ambient air at a first measurement zone of the aircraft and a second measurement unit 3 configured to measure a second pressure P of the ambient air, at a second measurement zone of the aircraft, the second pressure P having a value lower than the first static pressure Ps. The first measurement unit 2 measures the first static pressure with the aid of ns a probe for measuring static pressure, and in particular several measurement probes as described below. In the same way, the second measurement unit 3 measures the second pressure P using at least one static pressure measuring probe, called a static pressure probe. The device 1 also comprises a calculation unit 5 configured to estimate the Mach number using the following expression: the parameter k satisfying the expression k = Z (1-jp) in which Z is a dependent parameter the position of the second measurement zone on the aircraft. The data collected by the first and second measurement units 2 and 3 are transmitted to the calculation unit 5, respectively, via links 4 and 6.
    [0007] The device 1 further comprises a data transmission unit (link 8) configured to transmit the estimated Mach number to a user system 7, for example to a display unit or to an onboard system (or calculator). . Measuring zones of the first static pressure Ps and the second pressure P are chosen, which make it possible to obtain a difference in values between the first static pressure Ps and the second pressure P. In fact, the greater the difference between the value of the first static pressure Ps and the value of the second pressure P is important, the better is the estimate of the number of Mach M and therefore the CAS air speed of the aircraft. For this purpose, it is provided in particular to position the first measurement unit 2 at a location on the aircraft where the static pressure does not depend very much on the Mach number M and the second measurement unit 3 on a location of the aircraft. which, on the contrary, depends greatly on the number of Mach M. In other words, it is chosen to position the first measurement zone on the aircraft at a position less disturbed by the flow of air flowing over the aircraft than does the is the second zone.
    [0008] In addition, the larger the Mach number, the smaller the measurement of the second pressure P and the smaller the first static pressure Ps. The function Ps / P is therefore a monotonous and increasing function as a function of the Mach number. .
    [0009] Thus, the estimate of the Mach number is all the more precise as the Mach number is large - as long as the flow remains subsonic - and the quotient Ps / P is large. Therefore, preferably, to obtain the best possible accuracy and to maximize the range of validity of the estimate, the second measurement zone of the second pressure P is placed so as to maximize the quotient Ps / P. Thus, in knowing the value of the ratio between P and Ps, one is able to know the range of speeds inside which is the estimation of the speed of the aircraft.
    [0010] FIG. 2 illustrates an example of positioning of the first and second measurement zones 20 and 21 making it possible to obtain such a difference in values between the first static pressure Ps and the second pressure P. The first measurement zone 20 is located on the fuselage 15 of the aircraft 100. As explained above, the first measurement unit 2 comprises 20 at least one measurement probe located in the first measurement zone 20. In the embodiment illustrated in FIG. 2, the first unit 2 2 comprises a plurality of probes 11 and 12 and in particular two probes known as first and second probes 11 and 12 respectively measuring a first and a second intermediate static pressure Ps' and Ps ". computer (not shown) which is configured to determine the first static pressure Ps by preferably performing an average of the first and second presses ns intermediates Ps' and Ps "measured. In a particular embodiment of the invention, the first and the second intermediate static pressures Ps' and Ps "are measured, respectively, on either side of a longitudinal axis L of the aircraft 100 at the level of a first and a second intermediate measuring point It is understood here that the first and second probes 11 and 12 are located on either side of the longitudinal axis L of the aircraft 100. first variant shown in FIG. 2 of this particular embodiment, the first and second intermediate static pressures Ps' and Ps "are measured on the lateral sides of the aircraft 100. The first and second probes 11, 12 are then in this embodiment, the first static pressure Ps is measured by averaging two intermediate pressures Ps' and Ps "measured on the sides of the aircraft 100. By introducing the first static pressure in this way, the errors due to the skid angle of the aircraft are reduced. In a particular variant, the first and second intermediate static pressures Ps' and Ps "are measured on both sides of a vertical tail (not shown) of the aircraft 100.
    [0011] As shown in FIG. 2, the second measurement zone 21 (relative to the measurement unit 3) is located on the fuselage 15 of the aircraft 100. The second measurement zone 21 is in particular located in front of the first zone 20, because at this location of the aircraft 100, the measurement of the static pressure is more sensitive to the flow of air and the second measured pressure P will be lower than the first static pressure Ps. In this configuration , the parameter Z satisfies the following relation z = 2 in which Cpo is a Cpo * y constant pressure coefficient and y is the adiabatic index of air. Cpo does not depend on the number of Mach M, but on the shape of the object on which it is located. Alternatively, in a not shown embodiment, the second measurement zone 21 is located in the nacelle of a motor 10 of the aircraft 100. It is chosen to position the second measurement zone 21 in the nacelle of the engine 10 of the aircraft 100, because the second pressure P measured in this zone is lower than that measured in the first measurement zone located on the fuselage. The parameter Z then satisfies the following relationship Z = (aN1 + b) in which a and b are empirically determined constants and Ni represents the rotational speed of the blower of the motor 10.
    [0012] The constants a and b are determined empirically, in particular using measurements made during test flights. FIG. 3 schematically illustrates the calculation steps performed by the calculation unit 5 in the case where the second measurement unit 3 is located on the nacelle of the engine 10 of the aircraft. In the case where the second measurement unit 3 is placed on the fuselage 15 of the aircraft 100 as seen above, the expression aN1 + b in this figure 3 is replaced by a constant. The invention also makes it possible to position the second measuring zone 21 at other locations of the aircraft 100 allowing a measurement lower than the second pressure P with respect to the first static pressure Ps, for example at a vertical tail of the aircraft 100.
    权利要求:
    Claims (9)
    [0001]
    REVENDICATIONS1. A method for estimating the Mach number of an aircraft (100), characterized in that it comprises the following successive steps automatically consisting of: A) measuring a first static pressure Ps of ambient air at the level of a first measurement zone (20) located on the aircraft (100); B) measuring a second pressure P of the ambient air, by means of at least 10 a static pressure probe, at a second measurement zone (21) located on the aircraft (100), said second pressure P having a value lower than the first static pressure Ps; C) estimating a Mach number of the aircraft (100), using the following expression: the parameter k satisfying the expression k = Z (1 - in which Z is a parameter dependent on the position of the second measurement zone (21) on the aircraft (100), and D) transmitting the Mach number thus estimated to a user system (7). 20
    [0002]
    2. Method according to claim 1, wherein the second measurement zone (21) is located on a fuselage (15) of the aircraft (100), the parameter Z satisfying the following relationship z = 2 in which Cpo is a coefficient of Cpo * y constant pressure and y the adiabatic index of air.
    [0003]
    3. A method according to claim 1, wherein the second measurement zone (21) is located in the nacelle of an engine (10) of the aircraft (100), the parameter Z satisfying the following relationship Z = (aN1 b) where a and b are empirically determined constants and Ni is the rotational speed of the engine blower (10). 3024238
    [0004]
    A method according to any one of the preceding claims, wherein step A comprises substeps consisting of: Aa) measuring a first intermediate static pressure Ps' and a second intermediate static pressure Ps "in said first zone of 5 measuring (20), respectively, at a first intermediate measurement point and a second intermediate measurement point, and Ab) estimating the first static pressure Ps by averaging the first and second intermediate static pressures Ps' and Ps "measured in the previous step Aa). 10
    [0005]
    5. Method according to claim 4, wherein the first intermediate measurement point and the second intermediate measurement point are located on a fuselage (15) of the aircraft (100), respectively on either side of an axis. longitudinal (L) of the aircraft (100).
    [0006]
    6. Apparatus for estimating the Mach number of an aircraft, characterized in that it comprises: a first measurement unit (2) configured to measure a first static pressure Ps of the ambient air at a level of first measurement zone (20) of the aircraft (100); a second measurement unit (3) configured to measure a second pressure P of the ambient air, by means of at least one static pressure probe, at a second measurement zone (21) of the aircraft (100), the second pressure P having a value lower than the first static pressure Ps; a calculation unit (5) configured to estimate a Mach number of the aircraft (100), using the following expression: + 4k2 - k2 2 the parameter k satisfying the expression k Z (1 - wherein Z is a parameter dependent on the position of the second measurement zone (21) on the aircraft (100), and - a data transmission unit (8) configured to transmit the estimated Mach number to a system user (7) 302 42 3 8 11
    [0007]
    Aircraft comprising a device according to claim 6.
    [0008]
    An aircraft according to claim 7, wherein the first measurement unit (2) comprises first and second measurement probes (11, 12) configured to measure a first intermediate static pressure Ps' and a second intermediate static pressure Ps said first measurement unit (2) further comprising a computer configured to determine the first static pressure Ps by averaging the first and second intermediate static pressures Ps' and Ps ".
    [0009]
    9. Aircraft according to claim 8, wherein the first and second measurement probes (11, 12) are positioned on a fuselage (15) of the aircraft (100), on either side of an axis. longitudinal (L) of the aircraft (100).
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    引用文献:
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    法律状态:
    2015-06-26| PLFP| Fee payment|Year of fee payment: 2 |
    2016-01-29| PLSC| Search report ready|Effective date: 20160129 |
    2016-07-21| PLFP| Fee payment|Year of fee payment: 3 |
    2018-04-27| ST| Notification of lapse|Effective date: 20180330 |
    优先权:
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    FR1457105A|FR3024238B1|2014-07-23|2014-07-23|METHOD AND DEVICE FOR ESTIMATING THE NUMBER OF MACH OF AN AIRCRAFT|FR1457105A| FR3024238B1|2014-07-23|2014-07-23|METHOD AND DEVICE FOR ESTIMATING THE NUMBER OF MACH OF AN AIRCRAFT|
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