Flight air data measuring system

Abstract

The invention relates to the technical field of aviation. The inventive air data measuring system comprises a pitot pressure probe provided with sensing ports, an anti-freezing electric heater, a conduit, a pressure transducer, an outdoor air temperature sensor and an onboard computer; all the devices and parts are fixed in a streamlined housing attached to an aircraft and composed of an axial symmetric plane; the measuring system acquiring air data can be controlled automatically and interacts with the aircraft and other subsystems by electric connectors through an information interchange channel and power cords. In order to provide the system with more automation, the housing also comprises a power supply adapter. In order to extend the measuring range, reduce the structure weight and the required number of pressure measuring channels, the system comprises a pitot pressure probe which extends out convexly from the housing, is in a shape of small needle and is provided with sensing ports between the edges. In order to reduce the power required by the anti-freezing system and to simplify the structure design, the housing surface or a part thereof can be made of a hydrophobic material. In order to extend flight parameter measuring range, when the attack angle and the sideslip angle is -180 to 180 degrees, the whole range is covered.

Description

technical field [0001] The invention relates to the field of aviation technology, in particular to the acquisition of airborne flight data of aircraft. Background technique [0002] Measuring flight (airflow) parameters is one of the most important problems in aircraft aerodynamics. Currently, flight parameters are measured with pitot pressure probes, usually mounted on the fuselage or other aircraft components. Typically, an aircraft has multiple probes that measure local parameters that are almost entirely laminar. The determination of the true parameters is based on a preliminary calibration of the Pitot pressure probe. For light-sensitive aircraft in flight, the measurement of flight parameters is very important due to the significant expansion of the flight angle of attack and speed range (from low subsonic values ​​to hypersonic values). For helicopters in flight, flight parameter measurement is also very important, because the aircraft has high maneuverability char...

AI Technical Summary

Problems solved by technology

[0014] 1. "The system cannot be controlled automatically"

Monolithic units and components of the system are mounted outside and inside the fuselage; this greatly complicates troubleshooting problems

[0015] 2. “It takes a long time to detect system component failures”

[0016] 3. "Antifreeze systems require a lot of electricity"

The reason is that the Pitot pressure probes in the system must be mounted on the airframe so that the sensing port protrudes far beyond the boundary layer (to reduce errors due to total pressure loss); many types of aircraft are very large, so The pole length of the pitot pressure probe in the prior art is 150-200mm

For frost protection this results in a lot of power consumption - eg international standards specify 500W per pitot pressure probe and the total number of pitot pressure probes on civil aircraft should be 3 or 4

[0017] 4. "Complicated design of electric heaters for pitot pressure probes"

[0018] 5. "Equipment structure is particularly heavy"

This increases the total weight

[0019] 6. "Difficulty matching system design to changes in fuselage nose shape and / or different types of aircraft"

[0020] 7. "It takes a lot of time and cost to match the finished system to changes in the shape of the nose of the fuselage and / or to different types of aircraft"

but said system cannot fly backwards because the "forward looking" probes are buried in the split layer and / or thick boundary layer

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