FIELD: devices for storage and delivery of liquid components of propellants and fuels for spacecraft and flying vehicles.
SUBSTANCE: proposed device has frame with pressurization system and propellant tanks (fuel and oxidizer tanks) mounted on it. Each fuel tank has shell and inner elastic membrane. According to the first and second versions, inner elastic membrane is provided with spiral stiffener secured on its surface whose height smoothly comes to nothing. Besides that, surface of inner elastic membrane is provided with chute-like groove which is parallel to spiral stiffener. According to the first version, inner elastic membrane is secured to propellant tank shell and according to the second version, inner elastic membrane is secured to propellant tank shell by means of bellows. According to the third version, inner elastic membrane has varying thickness: its thickness gradually reduces from center to periphery of envelope to the point of securing it to propellant tank shell. Inner elastic membrane is made from corrosion-resistant plastic material.
EFFECT: avoidance of additional stresses in inner elastic membrane in case of repeated rearrangement; enhanced reliability and survivability.
4 cl,4 dwg
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Authors
Dates
2007-06-20—Published
2005-10-11—Filed