| 摘要 |
FIELD: aircraft engineering.SUBSTANCE: spacecraft electric power supply comprises solar batteries (SC), storage batteries (SB), stabilised voltage inverter (SVI) with charging and discharging inverters CI and DI and output voltage stabiliser (8) (OVS). SVI is designed to match operation of SC and SB and to allow stable supply of service systems and payload. In fabrication, SC (1) is detached from spacecraft (connectors (2) and (2-1), (3) and (3-1) being broken. SB (5) is connected "-" with minus bus and "+" is connected via terminals (5-2) and (5-1) (broken in circuit diagram) with CI and DI, (6) and (7), respectively. Instead of SC, its imitator (9) is connected via connectors (2-1) and (3-1) to SVI input (4) while SB imitator (10) is connected instead of SB (5) to CI (6) and DI (7). Additionally, imitator (10) is connected to spacecraft via remote capacitance filter (12) with capacitor unit (12-1) nearby CI (6) and DI (7). Capacity of filter (12) is selected experimentally on the basis of voltage ripple constriction level condition. Imitators (9) and (10) are supplied from industrial power supply line (9-1) and (10-1) and guaranteed power supply line (11/1) and (11/2).EFFECT: higher quality and reliability.2 cl, 1 dwg |
