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Hybrid rocket propulsion systems having any of the following: N.B.: SEE ALSO 9A109 AND 9A119. a. Total impulse capacity exceeding 1,1 MNs; or b. Thrust levels exceeding 220 kN in vacuum exit conditions.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M20A1bCode: 9A009Hybrid rocket propulsion systems having any of the following: N.B.: SEE ALSO 9A109 AND 9A119. a. Total impulse capacity exceeding 1,1 MNs; or b. Thrust levels exceeding 220 kN in vacuum exit conditions.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M20A1bCode: 9A009Hybrid rocket propulsion systems having any of the following: N.B.: SEE ALSO 9A109 AND 9A119. a. Total impulse capacity exceeding 1,1 MNs; or b. Thrust levels exceeding 220 kN in vacuum exit conditions.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M2A1c1Code: 9A009Hybrid rocket propulsion systems having any of the following: N.B.: SEE ALSO 9A109 AND 9A119. a. Total impulse capacity exceeding 1,1 MNs; or b. Thrust levels exceeding 220 kN in vacuum exit conditions.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M2A1c1Code: 9A009c. Nozzles with thrust levels exceeding 45 kN or nozzle throat erosion rates of less than 0,075 mm/s; d. Movable nozzle or secondary fluid injection thrust vector control systems, capable of any of the following: 1. Omni-axial movement exceeding ± 5°; 2. Angular vector rotations of 20°/s or more; or 3. Angular vector accelerations of 40°/s 2 or more
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M2A1eCode: 9A008c. Nozzles with thrust levels exceeding 45 kN or nozzle throat erosion rates of less than 0,075 mm/s; d. Movable nozzle or secondary fluid injection thrust vector control systems, capable of any of the following: 1. Omni-axial movement exceeding ± 5°; 2. Angular vector rotations of 20°/s or more; or 3. Angular vector accelerations of 40°/s 2 or more
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M2A1eCode: 9A008b. Filament-wound “composite” motor cases exceeding 0,61 m in diameter or having ‘structural efficiency ratios (PV/W)’ exceeding 25 km; Technical Note: ‘Structural efficiency ratio (PV/W)’ is the burst pressure (P) multiplied by the vessel volume (V) divided by the total pressure vessel weight (W).
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M3C2Code: 9A008b. Filament-wound “composite” motor cases exceeding 0,61 m in diameter or having ‘structural efficiency ratios (PV/W)’ exceeding 25 km; Technical Note: ‘Structural efficiency ratio (PV/W)’ is the burst pressure (P) multiplied by the vessel volume (V) divided by the total pressure vessel weight (W).
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M3C2Code: 9A008Components specially designed for solid rocket propulsion systems, as follows: N.B.: SEE ALSO 9A108. a. Insulation and propellant bonding systems, using liners to provide a ‘strong mechanical bond’ or a barrier to chemical migration between the solid propellant and case insulation material; Technical Note: ‘Strong mechanical bond’ means bond strength equal to or more than propellant strength.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M3C1Code: 9A008Components specially designed for solid rocket propulsion systems, as follows: N.B.: SEE ALSO 9A108. a. Insulation and propellant bonding systems, using liners to provide a ‘strong mechanical bond’ or a barrier to chemical migration between the solid propellant and case insulation material; Technical Note: ‘Strong mechanical bond’ means bond strength equal to or more than propellant strength.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M3C1Code: 9A008Components specially designed for solid rocket propulsion systems, as follows: N.B.: SEE ALSO 9A108. a. Insulation and propellant bonding systems, using liners to provide a ‘strong mechanical bond’ or a barrier to chemical migration between the solid propellant and case insulation material; Technical Note: ‘Strong mechanical bond’ means bond strength equal to or more than propellant strength.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M3A3Code: 9A008Components specially designed for solid rocket propulsion systems, as follows: N.B.: SEE ALSO 9A108. a. Insulation and propellant bonding systems, using liners to provide a ‘strong mechanical bond’ or a barrier to chemical migration between the solid propellant and case insulation material; Technical Note: ‘Strong mechanical bond’ means bond strength equal to or more than propellant strength.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M3A3Code: 9A008Solid rocket propulsion systems having any of the following: N.B.: SEE ALSO 9A107 AND 9A119. a. Total impulse capacity exceeding 1,1 MNs; b. Specific impulse of 2,4 kNs/kg or more, when the nozzle flow is expanded to ambient sea level conditions for an adjusted chamber pressure of 7 MPa; c. Stage mass fractions exceeding 88 % and propellant solid loadings exceeding 86 %; d. Components specified in 9A008; or e. Insulation and propellant bonding systems, using direct-bonded motor designs to provide a ‘strong mechanical bond’ or a barrier to chemical migration between the solid propellant and case insulation material. Technical Note: ‘Strong mechanical bond’ means bond strength equal to or more than propellant strength.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M2A1c1Code: 9A007Solid rocket propulsion systems having any of the following: N.B.: SEE ALSO 9A107 AND 9A119. a. Total impulse capacity exceeding 1,1 MNs; b. Specific impulse of 2,4 kNs/kg or more, when the nozzle flow is expanded to ambient sea level conditions for an adjusted chamber pressure of 7 MPa; c. Stage mass fractions exceeding 88 % and propellant solid loadings exceeding 86 %; d. Components specified in 9A008; or e. Insulation and propellant bonding systems, using direct-bonded motor designs to provide a ‘strong mechanical bond’ or a barrier to chemical migration between the solid propellant and case insulation material. Technical Note: ‘Strong mechanical bond’ means bond strength equal to or more than propellant strength.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M2A1c1Code: 9A007Solid rocket propulsion systems having any of the following: N.B.: SEE ALSO 9A107 AND 9A119. a. Total impulse capacity exceeding 1,1 MNs; b. Specific impulse of 2,4 kNs/kg or more, when the nozzle flow is expanded to ambient sea level conditions for an adjusted chamber pressure of 7 MPa; c. Stage mass fractions exceeding 88 % and propellant solid loadings exceeding 86 %; d. Components specified in 9A008; or e. Insulation and propellant bonding systems, using direct-bonded motor designs to provide a ‘strong mechanical bond’ or a barrier to chemical migration between the solid propellant and case insulation material. Technical Note: ‘Strong mechanical bond’ means bond strength equal to or more than propellant strength.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M2A1Code: 9A007Solid rocket propulsion systems having any of the following: N.B.: SEE ALSO 9A107 AND 9A119. a. Total impulse capacity exceeding 1,1 MNs; b. Specific impulse of 2,4 kNs/kg or more, when the nozzle flow is expanded to ambient sea level conditions for an adjusted chamber pressure of 7 MPa; c. Stage mass fractions exceeding 88 % and propellant solid loadings exceeding 86 %; d. Components specified in 9A008; or e. Insulation and propellant bonding systems, using direct-bonded motor designs to provide a ‘strong mechanical bond’ or a barrier to chemical migration between the solid propellant and case insulation material. Technical Note: ‘Strong mechanical bond’ means bond strength equal to or more than propellant strength.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M2A1Code: 9A007h. One-piece carbon-carbon thrust chambers or one-piece carbon-carbon exit cones, with densities exceeding 1,4 g/cm 3 and tensile strengths exceeding 48 MPa.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M3A10Code: 9A006h. One-piece carbon-carbon thrust chambers or one-piece carbon-carbon exit cones, with densities exceeding 1,4 g/cm 3 and tensile strengths exceeding 48 MPa.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M3A10Code: 9A006g. Liquid propellant injectors with individual orifices of 0,381 mm or smaller in diameter (an area of 1,14 × 10 –3 cm 2 or smaller for non-circular orifices) and specially designed for liquid rocket engines;
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M3A5Code: 9A006g. Liquid propellant injectors with individual orifices of 0,381 mm or smaller in diameter (an area of 1,14 × 10 –3 cm 2 or smaller for non-circular orifices) and specially designed for liquid rocket engines;
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M3A5Code: 9A006f. Propellant storage systems using the principle of capillary containment or positive expulsion (i.e., with flexible bladders);
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M3A8Code: 9A006f. Propellant storage systems using the principle of capillary containment or positive expulsion (i.e., with flexible bladders);
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M3A8Code: 9A006e. High-pressure (exceeding 10,6 MPa) thrust chambers and nozzles therefor;
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M3A10Code: 9A006e. High-pressure (exceeding 10,6 MPa) thrust chambers and nozzles therefor;
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M3A10Code: 9A0069A006
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M3A5Code: 9A0069A006
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M3A5Code: 9A006b. Cryogenic containers or closed-cycle refrigeration systems, capable of providing temperatures of 100 K (–173 °C) or less for “aircraft” capable of sustained flight at speeds exceeding Mach 3, launch vehicles or “spacecraft”; 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;
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M3A8Code: 9A006b. Cryogenic containers or closed-cycle refrigeration systems, capable of providing temperatures of 100 K (–173 °C) or less for “aircraft” capable of sustained flight at speeds exceeding Mach 3, launch vehicles or “spacecraft”; 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;
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M3A8Code: 9A006Liquid rocket propulsion systems containing any of the systems or components, specified in 9A006. N.B.: SEE ALSO 9A105 AND 9A119.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M20A1Code: 9A005Liquid rocket propulsion systems containing any of the systems or components, specified in 9A006. N.B.: SEE ALSO 9A105 AND 9A119.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M20A1Code: 9A005Liquid rocket propulsion systems containing any of the systems or components, specified in 9A006. N.B.: SEE ALSO 9A105 AND 9A119.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M2A1cCode: 9A005Liquid rocket propulsion systems containing any of the systems or components, specified in 9A006. N.B.: SEE ALSO 9A105 AND 9A119.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M2A1cCode: 9A005Liquid rocket propulsion systems containing any of the systems or components, specified in 9A006. N.B.: SEE ALSO 9A105 AND 9A119.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M2A1aCode: 9A005Liquid rocket propulsion systems containing any of the systems or components, specified in 9A006. N.B.: SEE ALSO 9A105 AND 9A119.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M2A1aCode: 9A005Space launch vehicles, “spacecraft”, “spacecraft buses”, “spacecraft payloads”, “spacecraft” on-board systems or equipment, and terrestrial equipment, as follows: N.B.: SEE ALSO 9A104. a. Space launch vehicles; b. “Spacecraft”; c. “Spacecraft buses”; d. “Spacecraft payloads” incorporating items specified in 3A001.b.1.a.4., 3A002.g., 5A001.a.1., 5A001.b.3., 5A002.a.5., 5A002.a.9., 6A002.a.1., 6A002.a.2., 6A002.b., 6A002.d., 6A003.b., 6A004.c., 6A004.e., 6A008.d., 6A008.e., 6A008.k., 6A008.l. or 9A010.c.; e. On-board systems or equipment, specially designed for “spacecraft” and having any of the following functions: 1. ‘Command and telemetry data handling’; Note: For the purpose of 9A004.e.1., ‘command and telemetry data handling’ includes bus data management, storage, and processing. 2. ‘Payload data handling’; or Note: For the purpose of 9A004.e.2., ‘payload data handling’ includes payload data management, storage, and processing. 3. ‘Attitude and orbit control’; Note: For the purpose of 9A004.e.3., ‘attitude and orbit control’ includes sensing and actuation to determine and control the position and orientation of a “spacecraft”. N.B.: For equipment specially designed for military use, see Military Goods Controls. f. Terrestrial equipment, specially designed for “spacecraft” as follows: 1. Telemetry and telecommand equipment; 2. Simulators.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M19A1Code: 9A004Space launch vehicles, “spacecraft”, “spacecraft buses”, “spacecraft payloads”, “spacecraft” on-board systems or equipment, and terrestrial equipment, as follows: N.B.: SEE ALSO 9A104. a. Space launch vehicles; b. “Spacecraft”; c. “Spacecraft buses”; d. “Spacecraft payloads” incorporating items specified in 3A001.b.1.a.4., 3A002.g., 5A001.a.1., 5A001.b.3., 5A002.a.5., 5A002.a.9., 6A002.a.1., 6A002.a.2., 6A002.b., 6A002.d., 6A003.b., 6A004.c., 6A004.e., 6A008.d., 6A008.e., 6A008.k., 6A008.l. or 9A010.c.; e. On-board systems or equipment, specially designed for “spacecraft” and having any of the following functions: 1. ‘Command and telemetry data handling’; Note: For the purpose of 9A004.e.1., ‘command and telemetry data handling’ includes bus data management, storage, and processing. 2. ‘Payload data handling’; or Note: For the purpose of 9A004.e.2., ‘payload data handling’ includes payload data management, storage, and processing. 3. ‘Attitude and orbit control’; Note: For the purpose of 9A004.e.3., ‘attitude and orbit control’ includes sensing and actuation to determine and control the position and orientation of a “spacecraft”. N.B.: For equipment specially designed for military use, see Military Goods Controls. f. Terrestrial equipment, specially designed for “spacecraft” as follows: 1. Telemetry and telecommand equipment; 2. Simulators.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M19A1Code: 9A004Space launch vehicles, “spacecraft”, “spacecraft buses”, “spacecraft payloads”, “spacecraft” on-board systems or equipment, and terrestrial equipment, as follows: N.B.: SEE ALSO 9A104. a. Space launch vehicles; b. “Spacecraft”; c. “Spacecraft buses”; d. “Spacecraft payloads” incorporating items specified in 3A001.b.1.a.4., 3A002.g., 5A001.a.1., 5A001.b.3., 5A002.a.5., 5A002.a.9., 6A002.a.1., 6A002.a.2., 6A002.b., 6A002.d., 6A003.b., 6A004.c., 6A004.e., 6A008.d., 6A008.e., 6A008.k., 6A008.l. or 9A010.c.; e. On-board systems or equipment, specially designed for “spacecraft” and having any of the following functions: 1. ‘Command and telemetry data handling’; Note: For the purpose of 9A004.e.1., ‘command and telemetry data handling’ includes bus data management, storage, and processing. 2. ‘Payload data handling’; or Note: For the purpose of 9A004.e.2., ‘payload data handling’ includes payload data management, storage, and processing. 3. ‘Attitude and orbit control’; Note: For the purpose of 9A004.e.3., ‘attitude and orbit control’ includes sensing and actuation to determine and control the position and orientation of a “spacecraft”. N.B.: For equipment specially designed for military use, see Military Goods Controls. f. Terrestrial equipment, specially designed for “spacecraft” as follows: 1. Telemetry and telecommand equipment; 2. Simulators.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M1A1Code: 9A004Space launch vehicles, “spacecraft”, “spacecraft buses”, “spacecraft payloads”, “spacecraft” on-board systems or equipment, and terrestrial equipment, as follows: N.B.: SEE ALSO 9A104. a. Space launch vehicles; b. “Spacecraft”; c. “Spacecraft buses”; d. “Spacecraft payloads” incorporating items specified in 3A001.b.1.a.4., 3A002.g., 5A001.a.1., 5A001.b.3., 5A002.a.5., 5A002.a.9., 6A002.a.1., 6A002.a.2., 6A002.b., 6A002.d., 6A003.b., 6A004.c., 6A004.e., 6A008.d., 6A008.e., 6A008.k., 6A008.l. or 9A010.c.; e. On-board systems or equipment, specially designed for “spacecraft” and having any of the following functions: 1. ‘Command and telemetry data handling’; Note: For the purpose of 9A004.e.1., ‘command and telemetry data handling’ includes bus data management, storage, and processing. 2. ‘Payload data handling’; or Note: For the purpose of 9A004.e.2., ‘payload data handling’ includes payload data management, storage, and processing. 3. ‘Attitude and orbit control’; Note: For the purpose of 9A004.e.3., ‘attitude and orbit control’ includes sensing and actuation to determine and control the position and orientation of a “spacecraft”. N.B.: For equipment specially designed for military use, see Military Goods Controls. f. Terrestrial equipment, specially designed for “spacecraft” as follows: 1. Telemetry and telecommand equipment; 2. Simulators.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M1A1Code: 9A004Aero gas turbine engines having any of the following: N.B.: SEE ALSO 9A101. a. Incorporating any of the “technologies” specified in 9E003.a., 9E003.h. or 9E003.i.; or Note 1: 9A001.a. does not control aero gas turbine engines which meet all of the following: a. Certified by the civil aviation authorities of one or more “participating states”; and b. Intended to power non-military manned aircraft for which any of the following has been issued by civil aviation authorities of one or more “participating states” for the aircraft with this specific engine type: 1. A civil type certificate; or 2. An equivalent document recognized by the International Civil Aviation Organisation (ICAO). Note 2: 9A001.a. does not control aero gas turbine engines designed for Auxiliary Power Units (APUs) approved by the civil aviation authority in a “participating state”. b. Designed to power an aircraft to cruise at Mach 1 or higher, for more than thirty minutes.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M3A1Code: 9A001Aero gas turbine engines having any of the following: N.B.: SEE ALSO 9A101. a. Incorporating any of the “technologies” specified in 9E003.a., 9E003.h. or 9E003.i.; or Note 1: 9A001.a. does not control aero gas turbine engines which meet all of the following: a. Certified by the civil aviation authorities of one or more “participating states”; and b. Intended to power non-military manned aircraft for which any of the following has been issued by civil aviation authorities of one or more “participating states” for the aircraft with this specific engine type: 1. A civil type certificate; or 2. An equivalent document recognized by the International Civil Aviation Organisation (ICAO). Note 2: 9A001.a. does not control aero gas turbine engines designed for Auxiliary Power Units (APUs) approved by the civil aviation authority in a “participating state”. b. Designed to power an aircraft to cruise at Mach 1 or higher, for more than thirty minutes.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M3A1Code: 9A001