«Актуальные вопросы в сфере социально-экономических, технических и естественных наук и информационных технологий» (3-4 апреля 2014г.)

Ponomar T. M., Davydov S. O., Timoshenko Zh. I.

Oles Honchar Dnipropetrovsk National University


The key feature of proper functionality of mesh systems which ensure continuity of fuel during the flight time of an aircraft is the lack of gas passing through the mesh elements throughout the duration of the flight, until all of the fuel has been exhausted. The existing methods for calculating design parameters of mesh systems that ensure continuity of fuel are focused on determining the level of dynamic effects on the mesh element during which gas doses not penetrate the mesh [3]. However, the process of gas penetrating the mesh elements and the peculiarity of the function of the systems ensuring continuity of fuel during this time is compelling.

The function of the system ensuring continuity of fuel of the mesh type after the gas has passed through the mesh elements occurs when predetermined circumstances of exploitation of the device allow the pressurized gas to penetrate through the mesh element. Some designs of systems of ensuring continuity of fuel [1; 2] include several mesh surfaces, through which the pressurized gas will pass as the fuel tank is emptied, which lay in the path of the fuel as it is being forced out of the fuel tank. Furthermore, woven mesh or perforated plates can be used as fuel vibration dampers. The gas penetrating mesh cells does not disrupt the function of the system that ensures continuity of fuel [3]. Finally, the operating conditions of some modern aircraft allow for limited penetration of pressurized gas through mesh elements, and its location under the mesh surface on the side of the fuel pick-up.

In the above mentioned situations, a portion of the mesh element is located entirely inside the gas phase, which, under unfavorable conditions, can lead to the complete drying of the mesh element. Under the given circumstances, the mesh system of ensuring continuity of fuel stops to function as a phase separator, which is highly unfavorable.

This article is dedicated to the study of internal and external factors, which affect the function of mesh system of ensuring continuity of fuel in a given situation, as well as the study of means of eliminating the possibility of the complete drying of the mesh element.

The list of references:

1. Regnier W. W. Design and development of a passive propellant management system / W. W. Regnier, D. A. Hess // J. of Spacecraft and Rockets. – 1978. – Vol. 15, № 5. – P. 299–304.

2. Rollins J. R. 23 years of surface tension propellant management system design, development, manufacture, test and operation / J. R. Rollins // AIAA Paper. – 1986. – № 833. – 9 p.

3. Давыдов С. А. Проникновение газа через сетчатые элементы системы обеспечения сплошности топлива космического ЛА / С. А. Давыдов // Авиационно-космическая техника и технология. – 2006. – № 2 (28). – С. 80–86.