FIELD: aviation.
SUBSTANCE: according to the present invention there is provided a device having a pipeline, which feeds thermostating medium into compartment, and diffuser for formation of operational fluid dynamics parametres of flow of the objects mounted in the compartment. The diffuser is replaceable and connected to the compartment shell through plug connection. This connection represents hollow supporting and mounting flange with a drive of its connection to the compartment shell and moving relative to the specified flange branch pipe. The specified diffuser is mounted on the branch pipe. The connection drive may be pneumatic or mechanical.
EFFECT: weight reduction owing to the exclusion of diffuser from compartment configuration and increase in weight of effective load to be lifted by launch vehicle.
3 cl, 4 dwg
Title | Year | Author | Number |
---|---|---|---|
METHOD OF ESTIMATION OF UNTIGHTNESS OF FLYING VEHICLE COMPARTMENT PROVIDED WITH DRAINAGE DEVICES | 2003 |
|
RU2246708C1 |
METHOD OF THERMOSTATTING OF INSTRUMENT MODULE OF SPACE LAUNCH VEHICLE NOSE CONE AND ONBOARD SYSTEM FOR REALIZATION OF THIS METHOD (VERSIONS) | 2004 |
|
RU2279377C2 |
METHOD FOR DETERMINATION OF FLOW-RATE CHARACTERISTICS OF DRAINAGE DEVICES OF FLIGHT VEHICLE COMPARTMENT AND SYSTEM FOR ITS REALIZATION | 2003 |
|
RU2253095C2 |
METHOD OF THERMOSTATTING ROCKET POD OBJECTS AND ONBOARD SYSTEM FOR REALIZATION OF THIS METHOD | 2004 |
|
RU2280596C2 |
DIFFUSER USED FOR THERMAL CONDITIONING OF CARRIER ROCKET OBJECTS (VERSIONS) | 2007 |
|
RU2353557C2 |
METHOD FOR THERMOSTATTING PAY LOAD AND INSTRUMENTS OF CONTROL SYSTEM OF SPACE HEAD OF CARRIER ROCKET, AND AIRBORNE SYSTEM USED FOR METHOD REALISATION | 2007 |
|
RU2353556C2 |
METHOD OF THERMOSTATTING OF ROCKET POD ITEMS AND ONBOARD SYSTEM FOR REALIZATION OF THIS METHOD | 2004 |
|
RU2285640C2 |
METHOD OF THERMOSTATIC CONTROL OVER CARRIER ROCKET COMPONENTS AND ONBOARD SYSTEM TO THIS END | 2009 |
|
RU2412874C1 |
METHOD OF DETERMINATION OF FLOW RATE CHARACTERISTICS OF DRAINAGE FACILITIES OF FLYING VEHICLE CASE AND SYSTEM FOR REALIZATION OF THIS METHOD | 2003 |
|
RU2267108C2 |
METHOD OF THERMOSTATTING OF INSTRUMENT BAY OF CRYOGENIC STAGE OF SPACE NOSE CONE OF LAUNCH VEHICLE AND ONBOARD SYSTEM FOR REALIZATION OF THIS METHOD | 2004 |
|
RU2290353C2 |
Authors
Dates
2009-09-27—Published
2007-08-02—Filed