FIELD: transport.
SUBSTANCE: invention relates to thermostatic control of carrier rocket components ,e.g. payload, control system, etc., in countdown cycle. Proposed method comprises injecting thermostatting medium (TM) along carrier rocket head nose cone or across it. Note here that TM flow rate vector is directed only toward head unit top or bottom. At the same time, TM flow is directed in peripheral directions perpendicular to said planes opposite the axis of symmetry of carrier rocket head. This provide for favorable variation of swirled TM rate and its flow over nose cone length. Onboard thermostatic control system diffuser may be turned about is axis of symmetry and is coupled with carrier rocket head by plug-in joint. Note here that diffuser is mounted so that its plane of symmetry is located in that of head unit that crosses head unit and diffuser axis of symmetry or at an angle to it.
EFFECT: improved operating performances suitable for diverse carrier rocket components.
3 cl, 12 dwg
| Title | Year | Author | Number |
|---|---|---|---|
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|
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| METHOD OF THERMOSTATTING ROCKET POD OBJECTS AND ONBOARD SYSTEM FOR REALIZATION OF THIS METHOD | 2004 |
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RU2673439C1 |
