RU2007120603A

RU2007120603A - DEVICE FOR REGULATING THE AIR HUMIDITY IN THE INHABITED COMPARTMENT OF THE MANUFACTURED SPACE UNIT

Info

Publication number: RU2007120603A
Application number: RU2007120603/11A
Authority: RU
Inventors: Владислав Александрович Цихоцкий (RU); Владислав Александрович Цихоцкий; Александр Моисеевич Рябкин (RU); Александр Моисеевич Рябкин; Александр Григорьевич Железняков (RU); Александр Григорьевич Железняков; Анатолий Петрович Елчин (RU); Анатолий Петрович Елчин; Алексей Анатольевич Нежурин (RU); Алексей Анатольевич Нежурин; Сергей Юрьевич Романов (RU); Сергей Юрьевич Романов; Александр Анатольевич Телегин (RU); Александр Анатольевич Телегин
Original assignee: Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" (RU); Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева"
Priority date: 2007-06-01
Filing date: 2007-06-01
Publication date: 2008-12-10
Also published as: RU2361789C2

Abstract

1. Устройство для регулирования влажности воздуха в обитаемом отсеке пилотируемого космического аппарата, включающее двухполостный газожидкостный теплообменник-конденсатор с промежуточным влагосборником, жидкостная полость которого связана с гидравлическим контуром системы терморегулирования пилотируемого космического аппарата, воздушная полость сообщена с объемом обитаемого отсека, а промежуточный влагосборник через насос откачки конденсата связан со сменным сборником конденсата системы терморегулирования пилотируемого космического аппарата, и вентиляторы, отличающееся тем, что оно дополнительно содержит как минимум два патрона с регенерируемым влагопоглощающим сорбентом, два регулятора потока воздуха, байпасный воздуховод с управляемой дроссельной заслонкой и распределительный кран, при этом каждый упомянутый патрон снабжен нагревателем сорбента, а вход в каждый из упомянутых патронов связан воздуховодами соответственно с первым и вторым выходами первого регулятора потока воздуха, вход которого через первый вентилятор сообщен с объемом обитаемого отсека, а выход каждого из упомянутых патронов сообщен воздуховодами соответственно с первым и вторым входами второго регулятора потока воздуха, один из выходов которого сообщен с объемом обитаемого отсека, а второй - с воздушной полостью двухполостного газожидкостного теплообменника-конденсатора с промежуточным влагосборником и далее через второй вентилятор - с объемом обитаемого отсека, кроме того, воздуховоды на входе в упомянутые патроны сообщены между собой байпасным воздуховодом с управляемой дроссельной заслонкой, а промежуточны1. A device for controlling air humidity in the inhabited compartment of a manned spacecraft, including a two-cavity gas-liquid heat exchanger-condenser with an intermediate moisture collector, the liquid cavity of which is connected to the hydraulic circuit of the thermal control system of the manned spacecraft, the air cavity is in communication with the volume of the inhabited compartment, and the intermediate moisture collector is through the pump condensate pumping is connected with a replaceable condensate collector of the manned space thermal control system of the apparatus, and fans, characterized in that it additionally contains at least two cartridges with a regenerable moisture-absorbing sorbent, two air flow regulators, a bypass duct with a controlled throttle and a distribution valve, each cartridge being equipped with a sorbent heater, and an entrance to each of the mentioned cartridges is connected by air ducts, respectively, with the first and second outputs of the first air flow regulator, the input of which through the first fan is communicated with the volume inhabited by ECA, and the output of each of the mentioned cartridges is communicated by air ducts, respectively, with the first and second inputs of the second air flow regulator, one of the outputs of which is connected with the volume of the inhabited compartment, and the second with the air cavity of the two-cavity gas-liquid heat exchanger-condenser with an intermediate moisture collector and then through the second fan - with the volume of the habitable compartment, in addition, the ducts at the entrance to the said cartridges are interconnected by a bypass duct with a controlled throttle, and intermediate

Claims

1. A device for controlling air humidity in the inhabited compartment of a manned spacecraft, including a two-cavity gas-liquid heat exchanger-condenser with an intermediate moisture collector, the liquid cavity of which is connected to the hydraulic circuit of the thermal control system of the manned spacecraft, the air cavity is in communication with the volume of the inhabited compartment, and the intermediate moisture collector is through the pump condensate pumping is connected with a replaceable condensate collector of the manned space thermal control system of the apparatus, and fans, characterized in that it additionally contains at least two cartridges with a regenerable moisture-absorbing sorbent, two air flow regulators, a bypass duct with a controlled throttle and a distribution valve, each cartridge being equipped with a sorbent heater, and an entrance to each of the mentioned cartridges is connected by air ducts, respectively, with the first and second outputs of the first air flow regulator, the input of which through the first fan is communicated with the volume inhabited by ECA, and the output of each of the mentioned cartridges is communicated by air ducts, respectively, with the first and second inputs of the second air flow regulator, one of the outputs of which is connected with the volume of the inhabited compartment, and the second with the air cavity of the two-cavity gas-liquid heat exchanger-condenser with an intermediate moisture collector and then through the second fan - with the volume of the habitable compartment, in addition, the ducts at the entrance to the said cartridges are interconnected by a bypass duct with a controlled throttle, and intermediate The moisture collector of the two-cavity gas-liquid heat exchanger-condenser through the distribution valve installed at the outlet of the condensate pump is additionally connected to the water recovery system of the manned spacecraft.