FIELD: spacecraft propellant equipment; systems for topping-up orbital stations, type MIR.
SUBSTANCE: proposed module has housing, frame with oxidizer and fuel tanks secured on it and respective fittings and tank pressurization system. Modules are provided with two-chamber bellows. One chamber of bellows is connected with tank pressurization system and other chamber is communicated with liquid cavity of respective tank. Bellows are secured on frame at perpendicular orientation of longitudinal axes of symmetry relative to longitudinal axis of symmetry of propellant module coinciding with direction of flight.
EFFECT: enhanced reliability due to avoidance of additional loads on tanks caused by temperature variations.
1 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| FUEL MODULE | 2006 |
|
RU2347723C2 |
| PROPELLANT MODULE | 2004 |
|
RU2266241C1 |
| COMPARTMENT OF REFUELING COMPONENTS | 2003 |
|
RU2276044C2 |
| COMPARTMENT FOR TOPPING-UP (REPLENISHMENT) COMPONENTS | 2003 |
|
RU2246430C1 |
| PROPELLANT MODULE | 2004 |
|
RU2270144C2 |
| EXPLOSION SYSTEM WITH SEPARATION OF LIQUID AND GAS FOR FILLING SPACECRAFT AT ORBIT | 2003 |
|
RU2265131C2 |
| COMPARTMENT FOR REPLENISHING COMPONENTS | 2003 |
|
RU2247685C1 |
| COMPARTMENT FOR COMPONENTS OF RECHARGING | 2001 |
|
RU2217359C2 |
| PROPELLANT MODULE | 2004 |
|
RU2266242C1 |
| DEVICE FOR LEAKAGE TEST OF PRESSURIZATION SYSTEM OF FUEL AND OXIDANT TANKS OF SPACE VEHICLE | 2003 |
|
RU2240523C2 |
