초록 ▼

The invention relates to the measurement of the total pressure of a fluid flow, especially the total pressure of the airflow surrounding an aircraft. The invention proposes to replace a pitot tube with a device in which at least two fluid streams are taken off from the flow. These streams are brough

The invention relates to the measurement of the total pressure of a fluid flow, especially the total pressure of the airflow surrounding an aircraft. The invention proposes to replace a pitot tube with a device in which at least two fluid streams are taken off from the flow. These streams are brought into contact with each other so as to be mutually slowed down in a region (11) where the pressure is measured. This measured pressure is representative of the total pressure (Pt).

대표청구항 ▼

The invention claimed is: 1. A device for measuring the total pressure (Pt) of a flow, comprising: at least a first channel and a second channel having a first fluid stream and a second fluid stream, respectively, flowing therethrough, wherein said fluid streams are taken off from the flow through

The invention claimed is: 1. A device for measuring the total pressure (Pt) of a flow, comprising: at least a first channel and a second channel having a first fluid stream and a second fluid stream, respectively, flowing therethrough, wherein said fluid streams are taken off from the flow through said first and second channels, and are brought into contact with each other so as to be mutually slowed down in a region; and means for measuring the pressure within said region. 2. The device as claimed in claim 1, wherein at least one of the channels has an upstream open end, which is approximately oriented along the axis of the flow. 3. The device as claimed in claim 2, wherein said channels are positioned upstream of said region. 4. The device as claimed in claim 3, wherein the upstream ends of said channels are approximately parallel. 5. The device as claimed in claim 4, wherein the channels each have a downstream open end, the downstream open ends face each other, and said region is located between the downstream open ends. 6. The device as claimed in claim 4, further comprising a hollow body in which said region is located and into which the channels run, wherein the hollow body includes orifices for discharging the fluid streams from the hollow body. 7. The device as claimed in claim 4, further comprising fixing means for fixing said channels relative to the skin of an aircraft. 8. The device as claimed in claim 4, further comprising orienting means for orienting said upstream end along the axis of the flow, said at least one of the channels being fastened to said orienting means. 9. The device as claimed in claim 3, wherein the channels each have a downstream open end, the downstream open ends face each other, and said region is located between the downstream open ends. 10. The device as claimed in claim 9, further comprising a hollow body in which said region is located and into which the channels run, wherein the hollow body includes orifices for discharging the fluid streams from the hollow body. 11. The device as claimed in claim 3, further comprising a hollow body in which said region is located and into which the channels run, wherein the hollow body includes orifices for discharging the fluid streams from the hollow body. 12. The device as claimed in claim 11, wherein the orifices of the hollow body are positioned in such a way that, when the channels are obstructed, a pressure approximately equal to the static pressure (Ps) of the flow obtains within the hollow body. 13. The device as claimed in claim 2, further comprising fixing means for fixing said channels relative to the skin of an aircraft. 14. The device as claimed in claim 2, further comprising orienting means for orienting said upstream end along the axis of the flow, said at least one of the channels being fastened to said orienting means. 15. A device for measuring the total pressure (Pt) of a flow, comprising: an annular channel having multiple fluid streams flowing therethrough, wherein said fluid streams are taken off annularly from the flow, guided through said annular channel, and are brought into contact with each other so as to be mutually slowed down in a region; and means for measuring the pressure within said region. 16. The device as claimed in claim 15, wherein the channel, near an upstream end thereof, has an approximately tubular shape. 17. The device as claimed in claim 15, wherein the channel, near a downstream end thereof, closes up around said region. 18. The device as claimed in claim 15, wherein the channel includes, at a downstream end thereof, orifices for discharging the fluid from said region. 19. The device as claimed in claim 15, wherein said device further includes means for measuring the temperature in said region. 20. The device as claimed in claim 13, said fixing means being sized such that said region is located away from any boundary layer formed by the skin of the aircraft. 21. The device as claimed in claim 1, wherein said device further includes means for measuring the temperature in said region.