FIELD: aerodynamic tests, applicable in rocket manufacturing and aviation for determination and control of flight aerodynamic loads on the compartments of flight vehicles and their components.
SUBSTANCE: the claimed method includes injection of thermostating medium in the compartment, used as working medium. The flow rate of this medium is so selected that the pressure differentials outside and inside the compartment in the ground conditions would correspond the pressure differentials acting on the compartment in the flight trajectory. The characteristics of interest of the drainage devices are determined according to the measured flow rates at the run over of the thermostating medium through each drainage device, pressure differentials and the medium temperature in the compartment. The non-tightness of the compartment is taken into account. According to the test results, a decision on finishing of the compartment, or a change of the quantity of the drainage devices operating in flight, may be taken.
EFFECT: enhanced accuracy of determination of the flow-rate characteristics of the drainage device, reliability of operation of the compartment, and reduced operating expenditures connected with the work.
2 cl, 5 dwg
Title | Year | Author | Number |
---|---|---|---|
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 ESTIMATION OF UNTIGHTNESS OF FLYING VEHICLE COMPARTMENT PROVIDED WITH DRAINAGE DEVICES | 2003 |
|
RU2246708C1 |
METHOD OF THERMOSTATTING OF ITEMS LOCATED IN SUCCESSION IN COMPARTMENTS OF LAUNCH VEHICLE NOSE CONE | 2005 |
|
RU2294864C2 |
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 |
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 THERMOSTATTING PAY LOAD AND INSTRUMENTS OF CONTROL SYSTEM OF SPACE HEAD OF CARRIER ROCKET, AND AIRBORNE SYSTEM USED FOR METHOD REALISATION | 2007 |
|
RU2353556C2 |
MODE OF TEMPERATURE CONTROL OF THE OBJECTS OF A ROCKET BLOCK | 2005 |
|
RU2292291C2 |
DIFFUSER USED FOR THERMAL CONDITIONING OF CARRIER ROCKET OBJECTS (VERSIONS) | 2007 |
|
RU2353557C2 |
METHOD OF CONTROL OF AERODYNAMIC LOADS ACTING OF FLYING VEHICLE CASE AND DEVICE FOR REALIZATION OF THIS METHOD (VERSIONS) | 1999 |
|
RU2145564C1 |
ROCKET-CARRIER ASCENT UNIT | 2007 |
|
RU2355607C1 |
Authors
Dates
2005-05-27—Published
2003-08-06—Filed