Maneuvering aircraft altitude and speed sensor modeling

Аuthors

Eskin V. I.^1*, Poluektov S. P.^2**, Rubinov V. I.^2***, Plotitsyn D. A.^2****, Afanasev A. S.^2*****

1. ,
2. Air force academy named after professor N.E. Zhukovskii and Y.A. Gagarin, Voronezh, Russia

*e-mail: kaf302@mai.ru
**e-mail: poluektov.sp@mail.ru
***e-mail: rubinov777@.mail.ru
****e-mail: plotitsin danil 90@yandex.ru
*****e-mail: afanasev_andrey_90@mail.ru

Abstract

The research subject matter is the mathematical model of maneuvering aircraft altitude and speed sensor.

The aim is to increase the altitude and speed measuring accuracy during the maneuverable aircraft flight while solving the problem of static air pressure perception.

The relevance of the work lies in the fact that altitude and speed parameters measuring accuracy requirements are increasing as related to their metrological characteristics, reliability and performance improvement. The situation is due to the need to meet mobility requirements, to ensure flights regularity and flight safety in conditions of vertical separation reduction. The vertical separation can be reduced only after the problem of the absolute barometric altitude measuring accuracy improvement is solved. But this requires the information channel altimetry revision and improvement. Due to the fact that the absolute barometric altitude is a function of the static pressure and airflow temperature, then applied to the scientific problem solved, the particular problem of above mentioned primary air parameters measurement accuracy improvement comes to the fore. In the article the results of on-board airflow static pressure measurement accuracy improvement possibility research are given.

As the main instrument in the course of simulation SolidWorks and ANSYS software packages were used. With the help of this software the instrumentation channel static pressure accuracy characteristics of different pitot-static tubes (standard and several examples of pitot-static tubes under development) at the altitudes of 5,000, 10,000 и 15,000 m at airflow to Mach 2,2 with the angle of attack to 30 degrees were obtained.

The results of standard pitot-static tube and pitot-static tube under development comparative analysis are given. The design modifications of the pitot-static tube under development static pressure chamber intake ducts are demonstrated.

The obtained results can be used for designing the on-board pitot-statiс tube with minimal errors in the measurement channel of the static pressure in a wide range of altitudes, velocities and angles of attack. This allows to recommend the proposed pitot-static tube for maneuverable aircraft.

Keywords:

relative aerodynamic error, simulation modeling, altitude and speed parameters, pitot-static tube, static pressure

References

1. Oleinik A.I. Aviakosmicheskoe priborostroenie. 2011. № 1. pp. 3-10.

2. Semenov A.V. Deponirovannaya rukopis',VINITI, №280-V2005, 28.02.2005.

3. Semenov A.V. Deponirovannaya rukopis', VINITI, №279-V2005, 28.02.2005.

Download