- List
- EU dual-use list – Annex I to Regulation (EU) 2021/821, updated annually
- Originating regime
- Thỏa ước Wassenaar
N.B. SEE ALSO 9A106, 9A108 AND 9A120.
a. Cryogenic refrigerators, flightweight dewars, cryogenic heat pipes or cryogenic systems, designed to restrict cryogenic fluid losses to less than 30 % per year;
b. Cryogenic containers or closed-cycle refrigeration systems, designed to maintain or produce temperatures less than or equal to 100 K (-173,15 °C);
c. Slush hydrogen storage or transfer systems;
d. High pressure (exceeding 17,5 MPa) turbo pumps, pump components or their associated gas generator or expander cycle turbine drive systems;
e. High-pressure (exceeding 10,6 MPa) thrust chambers and nozzles therefor;
f. Propellant storage systems using the principle of capillary containment or positive expulsion (i.e., with flexible bladders);
g. Liquid propellant injectors with individual orifices of 0,381 mm or smaller in diameter (an area of 1,14 × 10-3 cm2 or smaller for non-circular orifices) and specially designed for liquid rocket engines;
h. One-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.
a. Cryogenic refrigerators, flightweight dewars, cryogenic heat pipes or cryogenic systems, designed to restrict cryogenic fluid losses to less than 30 % per year;
b. Cryogenic containers or closed-cycle refrigeration systems, designed to maintain or produce temperatures less than or equal to 100 K (-173,15 °C);
c. Slush hydrogen storage or transfer systems;
d. High pressure (exceeding 17,5 MPa) turbo pumps, pump components or their associated gas generator or expander cycle turbine drive systems;
e. High-pressure (exceeding 10,6 MPa) thrust chambers and nozzles therefor;
f. Propellant storage systems using the principle of capillary containment or positive expulsion (i.e., with flexible bladders);
g. Liquid propellant injectors with individual orifices of 0,381 mm or smaller in diameter (an area of 1,14 × 10-3 cm2 or smaller for non-circular orifices) and specially designed for liquid rocket engines;
h. One-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.