Aerospace and Propulsion
Systems and components, specially designed for liquid rocket propulsion systems, as follows:
| Reference | Parameter | Threshold |
|---|---|---|
| 9A006.d | High pressure ( | > 17.5 MPa |
| 9A006.e | High-pressure ( | > 10.6 MPa |
| 9A006.h | with densities | > 1.4 g/cm |
| 9A006.h | with densities exceeding 1.4 g/cm3 and tensile strengths | > 48 MPa |
9A006.aCryogenic refrigerators, flightweight dewars, cryogenic heat pipes or cryogenic systems, designed to restrict cryogenic fluid losses to less than 30% per year;
9A006.bCryogenic containers or closed-cycle refrigeration systems, designed to maintain or produce temperatures less than or equal to 100 K (-173.15°C);
9A006.cSlush hydrogen storage or transfer systems;
9A006.dHigh pressure (exceeding 17.5 MPa) turbo pumps, pump components or their associated gas generator or expander cycle turbine drive systems;
9A006.eHigh-pressure (exceeding 10.6 MPa) thrust chambers and nozzles therefor;
9A006.fPropellant storage systems using the principle of capillary containment or positive expulsion (i.e., with flexible bladders);
9A006.gLiquid propellant injectors with individual orifices of 0.381 mm or smaller in diameter (an area of 1.14 x 10-3 cm2 or smaller for non-circular orifices) and specially designed for liquid rocket engines;
9A006.hOne-piece carbon-carbon thrust chambers or one-piece carbon-carbon exit cones, with densities exceeding 1.4 g/cm3 and tensile strengths exceeding 48 MPa.
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