초록 ▼

The invention pertains to a process for determining aerodynamic parameters of an airflow surrounding an aircraft. On the basis of at least two probes situated on the skin of the aircraft, each probe comprising means for measuring the local angle of attack (α loc i, αloc j), the process con

The invention pertains to a process for determining aerodynamic parameters of an airflow surrounding an aircraft. On the basis of at least two probes situated on the skin of the aircraft, each probe comprising means for measuring the local angle of attack (α loc i, αloc j), the process consists in determining the angle of attack (α) and/or sideslip (β) of the aircraft, as a function of the local angle of attack of each probe and of the aerodynamic field of the aircraft. The invention also pertains to a process for detecting a fault with a probe used to determine the aerodynamic parameters of the airflow surrounding an aircraft. This fault detection process consists in: determining for all the groups of two probes: the angle of attack and/or sideslip as a function of the local angles of attack and of the aerodynamic field of the aircraft, various values of the pressure coefficient of each probe as a function of the local angle of attack of each probe and of the aerodynamic field of the aircraft, the upstream infinity static pressure as a function of the pressure coefficient and of the local static pressure of one and the same probe and as a function of a measurement of the total pressure, intercomparing the values of upstream infinity static pressure, the angle of attack values and/or the angle of sideslip values.

대표청구항 ▼

The invention claimed is: 1. A process, comprising: determining aerodynamic parameters of an airflow surrounding an aircraft, on the basis of at least two probes situated on the skin of the aircraft, each said probe comprising means for measuring the local angle of attack (αloc i, αloc j)

The invention claimed is: 1. A process, comprising: determining aerodynamic parameters of an airflow surrounding an aircraft, on the basis of at least two probes situated on the skin of the aircraft, each said probe comprising means for measuring the local angle of attack (αloc i, αloc j), wherein said process comprises determining any one of the angle of attack (α ) and sideslip (β) of the aircraft, as a function of the local angle of attack of each said probe and of the aerodynamic field of the aircraft. 2. The process as claimed in claim 1, wherein each said probe further comprises means for measuring the local static pressure (Ps loci, Pslocj) and the process further comprises the steps of determining the upstream infinity static pressure (Ps) of the airflow surrounding the aircraft as a function of the local angle of attack (αloc i, αloc j), of the total pressure (Pt) , of the local static pressure (Psloc i, Pslocj) and of the aerodynamic field of the aircraft. 3. The process as claimed in claim 2, further comprising the steps of: determining the angle of attack (α) and sideslip (β ) as a function of the measured local angles of attack (αloc i, αloc j), and of the aerodynamic field of the aircraft; determining the pressure coefficient (Kpi, Kp j) of each said probe as a function of the local angle of attack (αloc i, αloc j) of each said probe and of the aerodynamic field of the aircraft; and determining the upstream infinity static pressure (Ps) as a function of the pressure coefficient (Kpi, Kpj) and of the local static pressure (Psloc i, Psloc j) of a said probe and as a function of the total pressure (Pt), a said pressure coefficient Kpi of a probe being expressed as follows: description="In-line Formulae" end="lead"Kp i=(Psloc i-Ps)/(Pt-Ps),description="In-line Formulae" end="tail" wherein Psloc i represents the local static pressure of the relevant probe, wherein Ps represents the upstream infinity static pressure, and wherein Pt represents the total pressure. 4. The process as claimed in claim 3, wherein a net of curves of constant angle of attack (α) and a net of curves of constant angle of sideslip (β) are determined as a function of the local angles of attack (αloc i, αloc j) on the basis of the aerodynamic field. 5. The process as claimed in claim 3, wherein a net of curves of constant angle of attack (α) and a net of curves of constant angle of sideslip (β) are determined as a function of the local angle of attack (αloc i, αloc j) of a said probe (i, j) and of the pressure coefficient (Kpi, Kpj) of said probe on the basis of the aerodynamic field. 6. A process for detecting a fault with a probe used to determine aerodynamic parameters of an airflow surrounding an aircraft on the basis of at least three probes situated on the skin of the aircraft, each said probe comprising means for measuring the local angle of attack (αloc i, αloc j, αloc k) and means for measuring the local static pressure Psloc i, Psloc j and Psloc k), the process comprising the steps of: determining for any group of two probes: (i) the angle of attack (αij, α ik, αjk) as a function of the local angles of attack (αloc i, αloc j, αloc k) and of the aerodynamic field of the aircraft; (ii) one or more values of the pressure coefficient (from Kpiαij to Kpkαjk) of each said probe (i, j, k) as a function of the local angle of attack (αloc i, αloc j, αloc k) of each said probe and of the aerodynamic field of the aircraft; (iii) the upstream infinity static pressure (from Ps iαij to Pskαjk) as a function of the pressure coefficient (from Kpiαij to Kpkαjk) and of the local static pressure (Psloc i, Ps loc j, Psloc k) of a said probe (i, j, k) and as a function of a measurement of the total pressure (Pt); intercomparing the values of upstream infinity static pressure as well as the values of the angle of attack (αij, αik, αjk); identifying a possible fault with a said probe by evaluating differences between the values of upstream infinity static pressure; identifying a possible fault with a said probe by evaluating differences between the values of upstream infinity static pressure (from Psiαij to Pskαjk) as well as between the values of angle of attack (αij, αjik, αjk), a said pressure coefficient Kpi of a probe being expressed as follows: description="In-line Formulae" end="lead"Kp i=(Psloc i-Ps)/(Pt-Ps),description="In-line Formulae" end="tail" wherein Psloc i represents the local static pressure of the relevant probe, wherein Ps represents the upstream infinity static pressure, and wherein Pt represents the total pressure. 7. A process for detecting a fault with a probe used to determine aerodynamic parameters of an airflow surrounding an aircraft on the basis of at least three probes situated on the skin of the aircraft, each said probe comprising means for measuring the local angle of attack (αloc i, αloc j, αloc j) and means for measuring the local static pressure (Psioc i, Ps loc j, Psloc k), the process comprising the steps of: determining for all the groups of two probes: the angle of sideslip (βij, βik, βjk) as a function of the local angles of attack (α loc i, αloc j, αloc k) and of the aerodynamic field of the aircraft; one or more values of the pressure coefficient (from Kp iβij to Kpkβjk) of each said probe (i, j, k) as a function of the local angle of attack (αloc i, α loc j, αloc k) of each said probe and of the aerodynamic field of the aircraft; (iii) the upstream infinity static pressure (from Ps iβij to Pskβjk) as a function of the pressure coefficient (from Kpiβij to Kpkβjk) and of the local static pressure (Psloc i, Ps loc j, Ps loc k) of a said probe (i, j, k) and as a function of a measurement of the total pressure (Pt); intercomparing the values of upstream infinity static pressure as well as the values of the angle of sideslip (βij , βik, βjk); identifying a possible fault with a said probe by evaluating differences between the values of upstream infinity static pressure (from Psiαij to Pskαjk) as well as between the values of angle of sideslip (βij, βik, β jk), a said pressure coefficient Kpi of a probe being expressed as follows: description="In-line Formulae" end="lead"Kp i=(Psloc i-Ps)/(Pt-Ps),description="In-line Formulae" end="tail" wherein Psloc i represents the local static pressure of the relevant probe, wherein Ps represents the upstream infinity static pressure, and wherein Pt represents the total pressure. 8. The process as claimed in claim 6, comprising the steps of detecting by a fault means for measuring local angle of attack (α loc i, αloc j, αloc k) when the angle of attack values (αij, αik, α jk) or the angle of sideslip values (βij, β ik, βjk) are not substantially equal. 9. The process as claimed in claim 7, wherein at least one of said probes comprises means for measuring a total pressure therefrom (Pti, Ptj, Ptk). 10. The process as claimed in claim 6, wherein a said fault is identified by the means for measuring the local angle of attack (αloc i, αloc j, αloc k) when the angle of attack values (αij, αik, αjk) or the angle of sideslip values (βij, βik, βjk) are not substantially equal, and wherein the intercomparison of the values of upstream infinity static pressure (from Psiαij to Pskαjk; from Ps iβij) makes it possible to locate a defective probe. 11. The process as claimed in claim 9, wherein a said fault is identified by a means for measuring the total pressure of a probe (Pti, Ptj, Ptk) when the measured values of total pressure are not substantially equal, and the defective means for measuring the total pressure (PT) are located through a value of total pressure (Ptj, Ptj, Ptk) substantially different from the others. 12. The process as claimed in claim 6, wherein a said fault is identified by a means for measuring the local static pressure (Ps loc i, Psloc j, Psloc k) when the angle of attack values (αij, αik, αjk) are substantially equal, the angle of sideslip values (βij, βik, βjk) are substantially equal, the values of the total pressure (Pti, Ptj, Ptk) are substantially equal, and when the values of the upstream infinity static pressure (from Psiαij to Pskαjk; from Ps iβij to Pskβjk) are not substantially equal, and the defective means for measuring the local static pressure (Psloc i, Psloc j, Psloc k) are located by comparison of the values of upstream infinity static pressure (from Psiαij to Pskαjk; from Psiβij to Pskβ jk). 13. The process as claimed in claim 7, wherein a said fault is identified by a means for measuring the total pressure of a probe (Pti, Ptj, Ptk) when the measured values of total pressure are not substantially equal, and the defective means for measuring the total pressure (PT) are located through a value of total pressure (Pti, Ptj, Ptk) substantially different from the others, wherein at least one probe comprises means for measuring the total pressure (Pti, Ptj, Ptk). 14. The process as claimed in claim 7, wherein a said fault is identified by the means for measuring the local static pressure (Ps loc i, Psloc j, Psloc k) when the angle of attack values (αij, αik, αjk) are substantially equal, the angle of sideslip values (βij, βik, βjk) are substantially equal, the values of the total pressure (Pti, Ptj, Ptk) are substantially equal, the values of the upstream infinity static pressure (from Psiαij to Pskαjk; from Psiβ ij to Pskβjk) are not substantially equal, and the defective means for measuring the local static pressure (Psloc i, Psloc j, Psloc k) are located by comparison of the values of upstream infinity static pressure (from Psiαij to Pskαjk; from Psiβij to Pskβ jk), wherein at least one probe comprises means for measuring the total pressure (Pti, Ptj, Ptk).