| 摘要 |
FIELD: aircraft engineering. ^ SUBSTANCE: invention relates to spacecraft thermal control. Proposed method comprises determining heat source power in thermal control circuit, measuring magnetically-sensitive coolant (XA) temperature at drop generator outlet (T0) and percolating generator magnetic collector inlet (KP) where at drops are connected into flow (T1). Difference in said temperatures is used to define required flow rate of XA whereat thermal powers of KP radiator and heat source are identical. Required flow rate of XA via KP is maintained to determine magnetisation of XA (HXA) at temperature TNV. Coolant temperature (T2) is measured at the point where XA extends from collector and HXA is defined at said temperature. Required HXA is determined at collector outlet for required XA flow rate with due allowance for pressure loss in heat control circuit. In case required HXA and actual HXA differs but in tolerable limits, required flow rate in KP is maintained. Otherwise, temperature T2 is varied to approximate inner HXA to required value. HXA is determined at new temperatures T1 and T2 are used to calculate current collector capacity for it to approximate to required flow rate of XA. Temperatures T0 and T1, HXA corresponding to them are continuously measured to define required FA flow rate at drop generator outlet at equal heat powers of KP radiator heat source. Again, temperature T2 is measured to determine HXA at it required for necessary XA flow rate. ^ EFFECT: efficient control over coolant flow rate in heat control circuit. ^ 1 dwg |
