RU2007122197A

RU2007122197A - METHOD FOR OPERATING A NICKEL-HYDROGEN BATTERY BATTERY AS A COMPOSITION OF A SPACE UNIT OF REFRIGERATED EXECUTION WITH RADIATION COOLING AND A SPACE DEVICE FOR ITS IMPLEMENTATION

Info

Publication number: RU2007122197A
Application number: RU2007122197/11A
Authority: RU
Inventors: Виктор Владимирович Коротких (RU); Виктор Владимирович Коротких
Priority date: 2007-06-13
Filing date: 2007-06-13
Publication date: 2008-12-20
Also published as: RU2371361C2

Abstract

1. Способ эксплуатации никель-водородной аккумуляторной батареи в составе космического аппарата негерметичного исполнения с радиационным охлаждением, заключающийся в проведении зарядов, разрядов, хранении в заряженном состоянии, контроле давления и температуры аккумуляторов и обеспечении температурного режима посредством локальных нагревателей, отличающийся тем, что определяют текущее тепловыделение аккумуляторной батареи, а тепловыделение нагревателей регулируют исходя из соотношенияQнагр+Qаб-Qpo=const,где Qнагр - текущее интегральное тепловыделение нагревателей;Qаб - текущее тепловыделение аккумуляторной батареи;Qpo - теплоотдача посредством радиационного охлаждения;const - установленное значение разницы расчетного тепловыделения и теплоотдачи;при этом при запуске космического аппарата величина const равна нулю, а в процессе эксплуатации космического аппарата (автоматически либо по командам с Земли) ее корректируют в большую или меньшую сторону, исходя из условия нахождения температуры аккумуляторной батареи в пределах установленных граничных значений.2. Космический аппарат для реализации способа по п.1, содержащий приборный блок, выполненный в виде прямоугольного параллелепипеда, устройства и приборы, установленные на внутренних сторонах параллелепипеда приборного блока, в том числе система терморегулирования для подвода и сброса тепла, содержащая локальные нагреватели и радиаторы-излучатели, система электропитания, состоящая из солнечной батареи, стабилизированного преобразователя напряжения, никель-водородных аккумуляторных батарей, с установленными на аккумуляторах аналоговых датчиками да1. A method of operating a nickel-hydrogen storage battery as part of a non-hermetic spacecraft with radiation cooling, which consists in conducting charges, discharges, storing in a charged state, monitoring the pressure and temperature of the batteries and ensuring the temperature regime by means of local heaters, characterized in that the current the heat generation of the battery, and the heat release of the heaters is regulated based on the ratio Qheat + Qab-Qpo = const, where Qheat is the current integral heat release of the heaters; Qab is the current heat release of the battery; Qpo is the heat transfer by means of radiation cooling; const is the set value of the difference between the calculated heat release and heat transfer; at the same time, when the spacecraft is launched, the const value is equal to zero, and during the operation of the spacecraft (automatically or by commands from the Earth) it is adjusted up or down, based on the condition of finding the temperature ry of the storage battery within the established limit values. 2. A spacecraft for implementing the method according to claim 1, comprising an instrument block made in the form of a rectangular parallelepiped, devices and instruments installed on the inner sides of the instrument block parallelepiped, including a thermal control system for supply and discharge of heat, containing local heaters and radiators-emitters , power supply system, consisting of a solar battery, stabilized voltage converter, nickel-hydrogen storage batteries, with analog sensors installed on batteries yes

Claims

1. The method of operation of a nickel-hydrogen storage battery in a spacecraft of a leaky design with radiation cooling, which consists in carrying out charges, discharges, storage in a charged state, monitoring the pressure and temperature of the batteries and ensuring the temperature regime by means of local heaters, characterized in that they determine the current heat dissipation of the battery, and heat dissipation of heaters is regulated based on the ratio

Qnag + Qab-Qpo = const,

where Qnagr is the current integral heat emission of heaters;

Qab - the current heat of the battery;

Qpo - heat transfer through radiation cooling;

const is the set value of the difference in the calculated heat release and heat transfer;

in this case, when the spacecraft is launched, the value of const is zero, and during the operation of the spacecraft (automatically or by commands from the Earth), it is corrected to a greater or lesser extent, based on the condition that the battery temperature is within the established boundary values.

2. A spacecraft for implementing the method according to claim 1, comprising an instrument block made in the form of a rectangular parallelepiped, devices and devices mounted on the inside of the instrument box parallelepiped, including a temperature control system for supplying and discharging heat, containing local heaters and radiators -emitters, power supply system consisting of a solar battery, a stabilized voltage converter, nickel-hydrogen storage batteries, with analogue batteries installed x pressure and temperature sensors, battery monitoring devices, as well as an on-board control system with an on-board computer, characterized in that the analogue pressure and temperature sensors are connected to the information exchange channel between the indicated stabilized voltage converter, thermal control system and the battery’s temperature monitoring device an on-board computer, which is equipped with a program that corrects the operation of local battery heaters s thermal control system, depending on the state of charge and operating modes batteries and temperature.