FIELD: surrounding medium ground control equipment in space engineering and rocketry.
SUBSTANCE: proposed method includes delivery of gas component to upper part of head module and discharge of this component from lower part of head module at excessive pressure built-up in head module. Device proposed for realization of this method includes flow divider of gas component fed to upper part of head module and transit main for delivery of gas component through launch vehicle. Flow divider is secured on upper part of nose fairing and gas component discharge hatch is available in lower part of this fairing.
EFFECT: enhanced cleanness of head module before removal of servicing tower.
3 cl, 1 dwg
| Title | Year | Author | Number |
|---|---|---|---|
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|
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| DEVICE TO CONTROL THERMAL CONDITIONS AND PURITY INSIDE NOSE CONE OF SPACE ROCKET AND METHOD OF ITS OPERATION | 2009 |
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| METHOD FOR PROVISION OF THERMAL CONDITIONS OF HEAD UNIT AS PART OF SPACE ROCKET AND DEVICE FOR ITS REALIZATION | 2004 |
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| THERMAL PROTECTION OF PAYLOAD ARRANGED IN ASSEMBLY-PROTECTIVE UNIT AND DEVICE TO THIS END | 2014 |
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