Наземная отработка капиллярных фазоразделителей на основе комбинированных… 1 УДК 629.7.036. 001.2 (082)

No abstract

The paper presents theoretical and experimental substantiation of the prospects to use materials of the new type, i.e. the combined porous-mesh materials (CPMM), in the in-tank devices (ITD) structures of spacecraft propulsion systems and upper stages to ensure multiple liquid-propellant rocket engine start in practical zero gravity. It is shown that CPMM operation was accompanied by phenomena that were missing, when using mesh materials previously used for this purpose, the so-called mesh separators (MS). It is concluded that at present it should be considered expedient to widely introduce CPMM in the ITD structure elements, since in this capacity the CPMM properties are noticeably superior to those of conventional MS. As a result, the ITD efficiency based on CPMM increases significantly, which finally makes it possible to minimize unusable fuel residues in the tanks and, thereby, increase the energy-mass efficiency of the aerial vehicle as a whole.

The paper introduces the results of theoretical studies of the process of liquid fuel deposition in liquid-propellant rocket engine tanks under conditions of free (undisturbed) orbital (suborbital) flight under the influence of a small pre-launch overload created by auxiliary engines before the liquid-propellant sustainer starting. In this work, we estimated the relaxation time of the free volume of liquid for the most unfavorable case, and the minimum supply of the covolume for the guaranteed starting and uninterrupted operation of the liquid-propellant rocket engine in zero gravity. Furthermore, we investigated the possibility of controlling the relaxation time with a gradual or stepwise starting operation. The proposed formula makes it possible at the design stage to assess the minimum supply of fuel, which can be in contact with the innertank device before starting the liquid-propellant sustainer in zero gravity in order to ensure the uninterrupted operation of the propulsion system.

The paper proposes a mathematical model to estimate boost gas parameters at filling the feeding lines dead-end zones of the pneumohydraulic systems (PHS) of the liquid-propellant rocket engines (LRE). These calculations are required in preliminary assessment of the design characteristics of the PHS feed lines designed to ensure operation of the LRE pneumoautomatic systems. Engineering methodology currently existing to solve this problem provides for solution of a system of ordinary differential equations and does not allow tracking alteration in pressure and temperature along the length of the dead-end zones at filling the PHS feed lines. The proposed model takes into account inhomogeneity of the flow parameters along the length of the dead-end zones, as well as the nonadiabaticity of the flow, i.e. it assumes presence of the heat exchange between the walls of the feeding line and the boost gas. The presented model was used to construct dependences of gas parameters alterations in the feeding line. Results obtained were compared with calculations according to the evaluation method, which is traditionally used in the engineering practice to solve this class of problems.