Turna R. Synthesis of two-phase mechanically pumped loop for thermal control means of space vehicle

Українська версія

Thesis for the degree of Candidate of Sciences (CSc)

State registration number

0421U102915

Applicant for

Specialization

  • 05.05.03 - Двигуни та енергетичні установки

14-05-2021

Specialized Academic Board

Д 64.062.02

National Aerospace University "Kharkiv Aviation Institute"

Essay

Object – heat transfer processes in microgravity conditions in two-phase thermal control systems of spacecraft with high-capacity power plants; goal – to develop methodological bases for designing two-phase heat transfer loops of thermal control system of high capacity space power plant; methods - methods of physical and mathematical modeling of thermophysical processes in space power plants, methods of measuring thermophysical parameters, methods of statistical processing of experimental results, as well as informal methods of optimizing efficiency parameters of two-phase loops components; results – the concept, the methods of designing the structure and parameters of thermal control system based on two-phase loops for space power plants with high dissipating power; novelty – for the first time justified requirements to design of heat dissipation subsystem of high-capacity space power plant (more than 10 kW) with direct-flow condensers, the implementation of which allows validate the subsystem on Earth without mandatory tests in microgravity conditions, for the first time experimentally obtained relationships of heat transfer during evaporation and boiling on surfaces of heat controlled accumulator heater covered with thin wetted capillary-porous structures from multilayer metal grids that allows to predict temperature of heater of heat controlled accumulator in microgravity conditions, for the first time dependence of limiting heat transport capacity of capillary structures of heat controlled accumulator for microgravity conditions on basis of ground experiments is obtained, which allows to perform functional tests of the accumulator on Earth, for the first time it was proved by calculation-theoretical means that in microgravity conditions for regulation of parameters of two-phase heat transfer loop smaller power of heater of heat controlled accumulator is required, than in experiments on Earth; the degree of implementation - implemented in JSC FED and in educational process of National Aerospace University Kharkiv Aviation Institute; field of application - aerospace.

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