| The corresponding systems, equipment and components as identified in Council Regulation (EC) No 428/2009 of 5 May 2009 setting up a Community regime for the control of exports, transfer, brokering and transit of dual-use items | Missile Technology Control Regime (M.TCR): Equipment, software and technology annex |
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| 9A001 | Aero 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.
| M3A1 | Turbojet and turbofan engines, as follows:
a. Engines having both of the following characteristics:
1. ‘ Maximum thrust value ’ greater than 400 N (achieved un-installed) excluding civil certified engines with a ‘ maximum thrust value ’ greater than 8,89 kN (achieved un-installed); and
2. Specific fuel consumption of 0,15 kg N –1 h –1 or less (at maximum continuous power at sea level static conditions using the ICAO standard atmosphere);
Technical Note: In 3.A.1.a.1., ‘ maximum thrust value ’ is the manufacturer's demonstrated maximum thrust for the engine type un-installed. The civil type certified thrust value will be equal to or less than the manufacturer's demonstrated maximum thrust for the engine type.
b. Engines designed or modified for systems specified in 1.A. or 19.A.2., regardless of thrust or specific fuel consumption.
Note: Engines specified in 3.A.1. may be exported as part of a manned aircraft or in quantities appropriate for replacement parts for a manned aircraft. |
| 9A004 | Space 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;
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;
| M1A1 | Complete rocket systems (including ballistic missile systems, space launch vehicles, and sounding rockets) capable of delivering at least a 500 kg “ payload ” to a “ range ” of at least 300 km. |
| M19A1 | Complete rocket systems (including ballistic missile systems, space launch vehicles, and sounding rockets), not specified in 1.A.1., capable of a “ range ” equal to or greater than 300 km. |
| 9A005 | Liquid rocket propulsion systems containing any of the systems or components, specified in 9A006.
N.B.: SEE ALSO 9A105 AND 9A119. | M2A1a | Individual rocket stages usable in the systems specified in 1.A.; |
| M2A1c | Rocket propulsion subsystems, usable in the systems specified in 1.A., as follows;
1. Solid propellant rocket motors or hybrid rocket motors having a total impulse capacity equal to or greater than 1,1 × 10 6 Ns;
2. Liquid propellant rocket engines or gel propellant rocket motors integrated, or designed or modified to be integrated, into a liquid propellant or gel propellant propulsion system which has a total impulse capacity equal to or greater than 1,1 × 10 6 Ns;
Note: Liquid propellant apogee engines or station-keeping engines specified in 2.A.1.c.2., designed or modified for use on satellites, may be treated as Category II, if the subsystem is exported subject to end-use statements and quantity limits appropriate for the excepted end-use stated above, when having a vacuum thrust not greater than 1kN. |
| M20A1 | Complete subsystems as follows:
a. Individual rocket stages, not specified in 2.A.1., usable in systems specified in 19.A.;
b. Rocket propulsion subsystems, not specified in 2.A.1., usable in the systems specified in 19.A.1., as follows:
1. Solid propellant rocket motors or hybrid rocket motors having a total impulse capacity equal to or greater than 8,41 × 10 5 Ns, but less than 1,1 × 10 6 Ns;
2. Liquid propellant rocket engines or gel propellant rocket motors integrated, or designed or modified to be integrated, into a liquid propellant or gel propellant propulsion system which has a total impulse capacity equal to or greater than 8,41 × 10 5 Ns, but less than 1,1 × 10 6 Ns;
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| 9A006 | Systems and components, specially designed for liquid rocket propulsion systems, as follows:
N.B.: SEE ALSO 9A106, 9A108 AND 9A120. a. Cryogenic refrigerators, flightweight dewars, cryogenic heat pipes or cryogenic systems, specially designed for use in space vehicles and capable of restricting cryogenic fluid losses to less than 30 % per year;
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b. 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;
| M3A8 | Liquid propellant tanks specially designed for the propellants controlled in Item 4.C. or other liquid propellants used in the systems specified in 1.A.1. |
| | M3A5 | Liquid, slurry and gel propellant (including oxidisers) control systems, and specially designed components therefor, usable in the systems specified in 1.A., designed or modified to operate in vibration environments greater than 10 g rms between 20 Hz and 2 kHz.
Notes: 1. The only servo valves, pumps and gas turbines specified in 3.A.5. are the following: a. Servo valves designed for flow rates equal to or greater than 24 litres per minute, at an absolute pressure equal to or greater than 7 MPa, that have an actuator response time of less than 100 ms.
b. Pumps, for liquid propellants, with shaft speeds equal to or greater than 8 000 rpm at the maximum operating mode or with discharge pressures equal to or greater than 7 MPa.
c. Gas turbines, for liquid propellant turbopumps, with shaft speeds equal to or greater than 8 000 rpm at the maximum operating mode.
2. Systems and components specified in 3.A.5. may be exported as part of a satellite. |
e. High-pressure (exceeding 10,6 MPa) thrust chambers and nozzles therefor; | M3A10 | Combustion chambers and nozzles for liquid propellant rocket engines usable in the subsystems specified in 2.A.1.c.2. or 20.A.1.b.2. |
f. Propellant storage systems using the principle of capillary containment or positive expulsion (i.e., with flexible bladders); | M3A8 | |
g. 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; | M3A5 | |
h. 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. | M3A10 | |
| 9A007 | Solid 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.
| M2A1 | Complete subsystems usable in the systems specified in 1.A., as follows:
a. Individual rocket stages usable in the systems specified in 1.A.;
b. Re-entry vehicles, and equipment designed or modified therefor, usable in the systems specified in 1.A., as follows, except as provided in the Note below 2.A.1. for those designed for non-weapon payloads:
1. Heat shields, and components therefor, fabricated of ceramic or ablative materials;
2. Heat sinks and components therefor, fabricated of light-weight, high heat capacity materials;
3. Electronic equipment specially designed for re-entry vehicles;
c. Rocket propulsion subsystems, usable in the systems specified in 1.A., as follows;
1. Solid propellant rocket motors or hybrid rocket motors having a total impulse capacity equal to or greater than 1,1 × 10 6 Ns;
2. Liquid propellant rocket engines or gel propellant rocket motors integrated, or designed or modified to be integrated, into a liquid propellant or gel propellant propulsion system which has a total impulse capacity equal to or greater than 1,1 × 10 6 Ns;
Note: Liquid propellant apogee engines or station-keeping engines specified in 2.A.1.c.2., designed or modified for use on satellites, may be treated as Category II, if the subsystem is exported subject to end-use statements and quantity limits appropriate for the excepted end-use stated above, when having a vacuum thrust not greater than 1kN. d. ‘ Guidance sets ’ , usable in the systems specified in 1.A., capable of achieving system accuracy of 3,33 % or less of the “ range ” (e.g. a ‘ CEP ’ of 10 km or less at a “ range ” of 300 km), except as provided in the Note below 2.A.1. for those designed for missiles with a “ range ” under 300 km or manned aircraft;
Technical Notes: 1. A ‘ guidance set ’ integrates the process of measuring and computing a vehicle's position and velocity (i.e. navigation) with that of computing and sending commands to the vehicle's flight control systems to correct the trajectory. 2. ‘ CEP ’ (circle of equal probability) is a measure of accuracy, defined as the radius of the circle centred at the target, at a specific range, in which 50 % of the payloads impact. e. Thrust vector control subsystems, usable in the systems specified in 1.A., except as provided in the Note below 2.A.1. for those designed for rocket systems that do not exceed the “ range ” / “ payload ” capability of systems specified in 1.A.;
Technical Note: 2.A.1.e. includes the following methods of achieving thrust vector control:
b. Fluid or secondary gas injection;
c. Movable engine or nozzle;
d. Deflection of exhaust gas stream (jet vanes or probes);
f. Weapon or warhead safing, arming, fuzing, and firing mechanisms, usable in the systems specified in 1.A., except as provided in the Note below 2.A.1. for those designed for systems other than those specified in 1.A.
Note: The exceptions in 2.A.1.b., 2.A.1.d., 2.A.1.e. and 2.A.1.f. above may be treated as Category II if the subsystem is exported subject to end-use statements and quantity limits appropriate for the excepted end-use stated above. Solid propellant rocket motors or hybrid rocket motors having a total impulse capacity equal to or greater than 1,1 × 10 6 Ns;
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| M2A1c1 | |
| 9A008 | Components 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.
| M3A3 | Rocket motor cases, ‘ insulation ’ components and nozzles therefor, usable in the systems specified in 1.A. or 19.A.1.
Technical Note: In 3.A.3. ‘ insulation ’ intended to be applied to the components of a rocket motor, i.e. the case, nozzle inlets, case closures, includes cured or semi-cured compounded rubber components comprising sheet stock containing an insulating or refractory material. It may also be incorporated as stress relief boots or flaps.
Note: Refer to 3.C.2. for ‘ insulation ’ material in bulk or sheet form. |
| M3C1 | ‘ Interior lining ’ usable for rocket motor cases in the subsystems specified in 2.A.1.c.1. or specially designed for subsystems specified in 20.A.1.b.1.
Technical Note: In 3.C.1. ‘ interior lining ’ suited for the bond interface between the solid propellant and the case or insulating liner is usually a liquid polymer based dispersion of refractory or insulating materials e.g. carbon filled HTPB or other polymer with added curing agents to be sprayed or screeded over a case interior.
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b. 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).
| M3C2 | ‘ Insulation ’ material in bulk form usable for rocket motor cases in the subsystems specified in 2.A.1.c.1. or specially designed for subsystems specified in 20.A.1.b.1.
Technical Note: In 3.C.2. ‘ insulation ’ intended to be applied to the components of a rocket motor, i.e. the case, nozzle inlets, case closures, includes cured or semi-cured compounded rubber sheet stock containing an insulating or refractory material. It may also be incorporated as stress relief boots or flaps specified in 3.A.3.
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c. 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
| M2A1e | Thrust vector control subsystems, usable in the systems specified in 1.A., except as provided in the Note below 2.A.1. for those designed for rocket systems that do not exceed the “ range ” / “ payload ” capability of systems specified in 1.A.;
Technical Note: 2.A.1.e. includes the following methods of achieving thrust vector control:
b. Fluid or secondary gas injection;
c. Movable engine or nozzle;
d. Deflection of exhaust gas stream (jet vanes or probes);
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| 9A009 | 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.
| M2A1c1 | Solid propellant rocket motors or hybrid rocket motors having a total impulse capacity equal to or greater than 1,1 × 10 6 Ns; |
| M20A1b | Rocket propulsion subsystems, not specified in 2.A.1., usable in the systems specified in 19.A.1., as follows:
1. Solid propellant rocket motors or hybrid rocket motors having a total impulse capacity equal to or greater than 8,41 × 10 5 Ns, but less than 1,1 × 10 6 Ns;
2. Liquid propellant rocket engines or gel propellant rocket motors integrated, or designed or modified to be integrated, into a liquid propellant or gel propellant propulsion system which has a total impulse capacity equal to or greater than 8,41 × 10 5 Ns, but less than 1,1 × 10 6 Ns;
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| 9A010 | Specially designed components, systems and structures, for launch vehicles, launch vehicle propulsion systems or “ spacecraft ” , as follows:
N.B.: SEE ALSO 1A002 AND 9A110. a. Components and structures, each exceeding 10 kg and specially designed for launch vehicles manufactured using any of the following: 1. “ Composite ” materials consisting of “ fibrous or filamentary materials ” specified in 1C0010.e. and resins specified in 1C008 or 1C009.b.;
2. Metal “ matrix ” “ composites ” reinforced by any of the following:
a. Materials specified in 1C007;
b. “ Fibrous or filamentary materials ” specified in 1C010; or
c. Aluminides specified in 1C002.a.; or
3. Ceramic “ matrix ” “ composite ” materials specified in 1C007;
Note: The weight cut-off is not relevant for nose cones. | M6A1 | Composite structures, laminates, and manufactures thereof, specially designed for use in the systems specified in 1.A., 19.A.1. or 19.A.2. and the subsystems specified in 2.A. or 20.A. |
b. Components and structures, specially designed for launch vehicle propulsion systems specified in 9A005 to 9A009 manufactured using any of the following: 1. “ Fibrous or filamentary materials ” specified in 1C010.e. and resins specified in 1C008 or 1C009.b.;
2. Metal “ matrix ” “ composites ” reinforced by any of the following:
a. Materials specified in 1C007;
b. “ Fibrous or filamentary materials ” specified in 1C010; or
c. Aluminides specified by 1C002.a.; or
3. Ceramic “ matrix ” “ composite ” materials specified in 1C007;
| M6A1 | Composite structures, laminates, and manufactures thereof, specially designed for use in the systems specified in 1.A., 19.A.1. or 19.A.2. and the subsystems specified in 2.A. or 20.A. |
c. Structural components and isolation systems, specially designed to control actively the dynamic response or distortion of “ spacecraft ” structures; | M6A1 | Composite structures, laminates, and manufactures thereof, specially designed for use in the systems specified in 1.A., 19.A.1. or 19.A.2. and the subsystems specified in 2.A. or 20.A. |
d. Pulsed liquid rocket engines with thrust-to-weight ratios equal to or more than 1 kN/kg and a response time (the time required to achieve 90 % of total rated thrust from start-up) of less than 30 ms. | M3A2 | Ramjet/scramjet/pulse jet/ ‘ combined cycle engines ’ , including devices to regulate combustion, and specially designed components therefor, usable in the systems specified in 1.A. or 19.A.2.
Technical Note: In Item 3.A.2., ‘ combined cycle engines ’ are the engines that employ two or more cycles of the following types of engines: gas-turbine engine (turbojet, turboprop, turbofan and turboshaft), ramjet, scramjet, pulse jet, pulse detonation engine, rocket motor (liquid/solid-propellant and hybrid).
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| 9A011 | Ramjet, scramjet or combined cycle engines, and specially designed components therefor.
N.B.: SEE ALSO 9A111 AND 9A118. | M3A2 | Ramjet/scramjet/pulse jet/ ‘ combined cycle engines ’ , including devices to regulate combustion, and specially designed components therefor, usable in the systems specified in 1.A. or 19.A.2.
Technical Note: In Item 3.A.2., ‘ combined cycle engines ’ are the engines that employ two or more cycles of the following types of engines: gas-turbine engine (turbojet, turboprop, turbofan and turboshaft), ramjet, scramjet, pulse jet, pulse detonation engine, rocket motor (liquid/solid-propellant and hybrid).
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| 9A012 | “ Unmanned aerial vehicles ” ( “ UAVs ” ), unmanned “ airships ” , related equipment and components, as follows:
N.B.: SEE ALSO 9A112. a. “ UAVs ” or unmanned “ airships ” , designed to have controlled flight out of the direct ‘ natural vision ’ of the ‘ operator ’ and having any of the following:
1. Having all of the following:
a. A maximum ‘ endurance ’ greater than or equal to 30 minutes but less than 1 hour; and
b. Designed to take-off and have stable controlled flight in wind gusts equal to or exceeding 46,3 km/h (25 knots); or
2. A maximum ‘ endurance ’ of 1 hour or greater;
Technical Notes: 1. For the purposes of 9A012.a., ‘ operator ’ is a person who initiates or commands the “ UAV ” or unmanned “ airship ” flight. 2. For the purposes of 9A012.a., ‘ endurance ’ is to be calculated for ISA conditions (ISO 2533:1975) at sea level in zero wind. 3. For the purposes of 9A012.a., ‘ natural vision ’ means unaided human sight, with or without corrective lenses. b. Related equipment and components, as follows:
| M1A2 | Complete unmanned aerial vehicle systems (including cruise missile systems, target drones and reconnaissance drones) capable of delivering at least a 500 kg “ payload ” to a “ range ” of at least 300 km. |
| M19A | ITEM 19 OTHER COMPLETE DELIVERY SYSTEMS: equipment, assemblies and components |
3. Equipment or components, specially designed to convert a manned “ aircraft ” or manned “ airship ” , to a “ UAV ” or unmanned “ airship ” , specified in 9A012.a.;
4. Air breathing reciprocating or rotary internal combustion type engines, specially designed or modified to propel “ UAVs ” or unmanned “ airships ” , at altitudes above 15 240 metres ( 50 000 feet).
| M9A6 | Inertial or other equipment using accelerometers specified in 9.A.3. or 9.A.5. or gyros specified in 9.A.4. or 9.A.5., and systems incorporating such equipment, and specially designed components therefor. |
| 9A101 | Turbojet and turbofan engines, other than those specified in 9A001, as follows;
a. Engines having both of the following characteristics:
1. ‘ Maximum thrust value ’ greater than 400 N (achieved un-installed) excluding civil certified engines with a ‘ maximum thrust value ’ greater than 8 890 N (achieved un-installed), and
2. Specific fuel consumption of 0,15 kg/N/hr or less (at maximum continuous power at sea level static conditions using the ICAO standard atmosphere);
Technical Note: For the purpose of 9A101.a.1. ‘ maximum thrust value ’ is the manufacturer's demonstrated maximum thrust for the engine type un-installed. The civil type certified thrust value will be equal or less than the manufacturer's demonstrated maximum thrust for the engine type.
b. Engines designed or modified for use in “ missiles ” or unmanned aerial vehicles specified in 9A012 or 9A112.a.,
| M3A1 | Turbojet and turbofan engines, as follows:
a. Engines having both of the following characteristics:
1. ‘ Maximum thrust value ’ greater than 400 N (achieved un-installed) excluding civil certified engines with a ‘ maximum thrust value ’ greater than 8,89 kN (achieved un-installed); and
2. Specific fuel consumption of 0,15 kg N –1 h –1 or less (at maximum continuous power at sea level static conditions using the ICAO standard atmosphere);
Technical Note: In 3.A.1.a.1., ‘ maximum thrust value ’ is the manufacturer's demonstrated maximum thrust for the engine type un-installed. The civil type certified thrust value will be equal to or less than the manufacturer's demonstrated maximum thrust for the engine type.
b. Engines designed or modified for systems specified in 1.A. or 19.A.2., regardless of thrust or specific fuel consumption.
Note: Engines specified in 3.A.1. may be exported as part of a manned aircraft or in quantities appropriate for replacement parts for a manned aircraft. |
| 9A102 | ‘ Turboprop engine systems ’ specially designed for unmanned aerial vehicles specified in 9A012 or 9A112.a., and specially designed components therefor, having a ‘ maximum power ’ greater than 10 kW.
Note: 9A102 does not control civil certified engines. Technical Notes: 1. For the purposes of 9A102 a ‘ turboprop engine system ’ incorporates all of the following: a. Turboshaft engine; and
b. Power transmission system to transfer the power to a propeller.
2. For the purposes of 9A102 the ‘ maximum power ’ is achieved uninstalled at sea level static conditions using ICAO standard atmosphere. | M3A9 | ‘ Turboprop engine systems ’ specially designed for the systems in 1.A.2. or 19.A.2., and specially designed components therefor, having a maximum power greater than 10 kW (achieved uninstalled at sea level static conditions using the ICAO standard atmosphere), excluding civil certified engines.
Technical Note: For the purposes of Item 3.A.9., a ‘ turboprop engine system ’ incorporates all of the following: a. Turboshaft engine; and b. Power transmission system to transfer the power to a propeller.
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| 9A104 | Sounding rockets, capable of a range of at least 300 km.
N.B.: SEE ALSO 9A004. | M1A1 | Complete rocket systems (including ballistic missile systems, space launch vehicles, and sounding rockets) capable of delivering at least a 500 kg “ payload ” to a “ range ” of at least 300 km. |
| M19A1 | Complete rocket systems (including ballistic missile systems, space launch vehicles, and sounding rockets), not specified in 1.A.1., capable of a “ range ” equal to or greater than 300 km. |
| 9A105 | Liquid propellant rocket engines, as follows:
N.B.: SEE ALSO 9A119. | | |
a. Liquid propellant rocket engines usable in “ missiles ” , other than those specified in 9A005, integrated, or designed or modified to be integrated, into a liquid propellant propulsion system which has a total impulse capacity equal to or greater than 1,1 MNs; | M2A1c2 | Liquid propellant rocket engines or gel propellant rocket motors integrated, or designed or modified to be integrated, into a liquid propellant or gel propellant propulsion system which has a total impulse capacity equal to or greater than 1,1 × 10 6 Ns; |
b. Liquid propellant rocket engines, usable in complete rocket systems or unmanned aerial vehicles, capable of a range of 300 km, other than those specified in 9A005 or 9A105.a., integrated, or designed or modified to be integrated, into a liquid propellant propulsion system which has a total impulse capacity equal to or greater than 0,841 MNs | M20A1b2 | Liquid propellant rocket engines or gel propellant rocket motors integrated, or designed or modified to be integrated, into a liquid propellant or gel propellant propulsion system which has a total impulse capacity equal to or greater than 8,41 × 10 5 Ns, but less than 1,1 × 10 6 Ns |
| 9A106 | Systems or components, other than those specified in 9A006 as follows, specially designed for liquid rocket propulsion systems:
a. Ablative liners for thrust or combustion chambers, usable in “ missiles ” , space launch vehicles specified in 9A004 or sounding rockets specified in 9A104;
b. Rocket nozzles, usable in “ missiles ” , space launch vehicles specified in 9A004 or sounding rockets specified in 9A104;
| M3A3 | Rocket motor cases, ‘ insulation ’ components and nozzles therefor, usable in the systems specified in 1.A. or 19.A.1.
Technical Note: In 3.A.3. ‘ insulation ’ intended to be applied to the components of a rocket motor, i.e. the case, nozzle inlets, case closures, includes cured or semi-cured compounded rubber components comprising sheet stock containing an insulating or refractory material. It may also be incorporated as stress relief boots or flaps.
Note: Refer to 3.C.2. for ‘ insulation ’ material in bulk or sheet form. |
c. Thrust vector control sub-systems, usable in “ missiles ” ; Technical Note: Examples of methods of achieving thrust vector control specified in 9A106.c. are:
2. Fluid or secondary gas injection;
3. Movable engine or nozzle;
4. Deflection of exhaust gas stream (jet vanes or probes); or
| M2A1e | Thrust vector control subsystems, usable in the systems specified in 1.A., except as provided in the Note below 2.A.1. for those designed for rocket systems that do not exceed the “ range ” / “ payload ” capability of systems specified in 1.A.; Technical
Technical Note: 2.A.1.e. includes the following methods of achieving thrust vector control:
b. Fluid or secondary gas injection;
c. Movable engine or nozzle;
d. Deflection of exhaust gas stream (jet vanes or probes);
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d. Liquid, slurry and gel propellant (including oxidisers) control systems, and specially designed components therefor, usable in “ missiles ” , designed or modified to operate in vibration environments greater than 10 g rms between 20 Hz and 2 kHz; Note: The only servo valves, pumps and gas turbines specified in 9A106.d., are the following: a. Servo valves designed for flow rates equal to or greater than 24 litres per minute, at an absolute pressure equal to or greater than 7 MPa, that have an actuator response time of less than 100 ms;
b. Pumps, for liquid propellants, with shaft speeds equal to or greater than 8 000 r.p.m. at a maximum operating mode or with discharge pressures equal to or greater than 7 MPa.
c. Gas turbines, for liquid propellant turbopumps, with shaft speeds equal to or greater than 8 000 r.p.m. at the maximum operating mode.
| M3A5 | Liquid, slurry and gel propellant (including oxidisers) control systems, and specially designed components therefor, usable in the systems specified in 1.A., designed or modified to operate in vibration environments greater than 10 g rms between 20 Hz and 2 kHz.
Notes: 1. The only servo valves, pumps and gas turbines specified in 3.A.5. are the following: a. Servo valves designed for flow rates equal to or greater than 24 litres per minute, at an absolute pressure equal to or greater than 7 MPa, that have an actuator response time of less than 100 ms.
b. Pumps, for liquid propellants, with shaft speeds equal to or greater than 8 000 rpm at the maximum operating mode or with discharge pressures equal to or greater than 7 MPa.
c. Gas turbines, for liquid propellant turbopumps, with shaft speeds equal to or greater than 8 000 rpm at the maximum operating mode.
2. Systems and components specified in 3.A.5. may be exported as part of a satellite. |
e. Combustion chambers and nozzles, usable in “ missiles ” , space launch vehicles specified in 9A004 or sounding rockets specified in 9A104. | M3A10 | Combustion chambers and nozzles for liquid propellant rocket engines usable in the subsystems specified in 2.A.1.c.2. or 20.A.1.b.2. |
| 9A107 | Solid propellant rocket engines, usable in complete rocket systems or unmanned aerial vehicles, capable of a range of 300 km, other than those specified in 9A007, having total impulse capacity equal to or greater than 0,841 MNs.
N.B.: SEE ALSO 9A119. | M20A1b1 | Solid propellant rocket motors or hybrid rocket motors having a total impulse capacity equal to or greater than 8,41 × 10 5 Ns, but less than 1,1 × 10 6 Ns; |
| 9A108 | Components, other than those specified in 9A008, as follows, specially designed for solid rocket propulsion systems:
a. Rocket motor cases and “ insulation ” components therefor, usable in “ missiles ” , space launch vehicles specified in 9A004 or sounding rockets specified in 9A104;
b. Rocket nozzles, usable in “ missiles ” , space launch vehicles specified in 9A004 or sounding rockets specified in 9A104;
| M3A3 | Rocket motor cases, ‘ insulation ’ components and nozzles therefor, usable in the systems specified in 1.A. or 19.A.1. |
| M3A3 | Technical Note: In 3.A.3. ‘ insulation ’ intended to be applied to the components of a rocket motor, i.e. the case, nozzle inlets, case closures, includes cured or semi-cured compounded rubber components comprising sheet stock containing an insulating or refractory material. It may also be incorporated as stress relief boots or flaps.
Note: Refer to 3.C.2. for ‘ insulation ’ material in bulk or sheet form. |
c. Thrust vector control sub-systems, usable in “ missiles ” . Technical Note: Examples of methods of achieving thrust vector control specified in 9A108.c. are:
2. Fluid or secondary gas injection;
3. Movable engine or nozzle;
4. Deflection of exhaust gas stream (jet vanes or probes); or
| M2A1e | Thrust vector control subsystems, usable in the systems specified in 1.A., except as provided in the Note below 2.A.1. for those designed for rocket systems that do not exceed the “ range ” / “ payload ” capability of systems specified in 1.A.;
Technical Note: 2.A.1.e. includes the following methods of achieving thrust vector control:
b. Fluid or secondary gas injection;
c. Movable engine or nozzle;
d. Deflection of exhaust gas stream (jet vanes or probes);
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| 9A109 | Hybrid rocket motors and specially designed components as follows:
a. Hybrid rocket motors usable in complete rocket systems or unmanned aerial vehicles, capable of 300 km, other than those specified in 9A009, having a total impulse capacity equal to or greater than 0,841 MNs, and specially designed components therefor;
b. Specially designed components for hybrid rocket motors specified in 9A009 that are usable in “ missiles ” .
N.B.: SEE ALSO 9A009 and 9A119. | M3A6 | Specially designed components for hybrid rocket motors specified in 2.A.1.c.1. and 20.A.1.b.1. |
| M20A1b | Rocket propulsion subsystems, not specified in 2.A.1., usable in the systems specified in 19.A.1., as follows:
1. Solid propellant rocket motors or hybrid rocket motors having a total impulse capacity equal to or greater than 8,41 × 10 5 Ns, but less than 1,1 × 10 6 Ns;
2. Liquid propellant rocket engines or gel propellant rocket motors integrated, or designed or modified to be integrated, into a liquid propellant or gel propellant propulsion system which has a total impulse capacity equal to or greater than 8,41 × 10 5 Ns, but less than 1,1 × 10 6 Ns;
|
| M2A1c | Rocket propulsion subsystems, usable in the systems specified in 1.A., as follows;
1. Solid propellant rocket motors or hybrid rocket motors having a total impulse capacity equal to or greater than 1,1 × 10 6 Ns;
2. Liquid propellant rocket engines or gel propellant rocket motors integrated, or designed or modified to be integrated, into a liquid propellant or gel propellant propulsion system which has a total impulse capacity equal to or greater than 1,1 × 10 6 Ns;
Note: Liquid propellant apogee engines or station-keeping engines specified in 2.A.1.c.2., designed or modified for use on satellites, may be treated as Category II, if the subsystem is exported subject to end-use statements and quantity limits appropriate for the excepted end-use stated above, when having a vacuum thrust not greater than 1kN. |
| 9A110 | Composite structures, laminates and manufactures thereof, other than those specified in 9A010, specially designed for use in ‘ missiles ’ or the subsystems specified in 9A005, 9A007, 9A105, 9A106.c., 9A107, 9A108.c., 9A116 or 9A119.
N.B.: SEE ALSO 1A002. Technical Note: In 9A110 ‘ missile ’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.
| M6A1 | Composite structures, laminates, and manufactures thereof, specially designed for use in the systems specified in 1.A., 19.A.1. or 19.A.2. and the subsystems specified in 2.A. or 20.A. |
| 9A111 | Pulse jet engines, usable in “ missiles ” or unmanned aerial vehicles specified in 9A012 or 9A112.a., and specially designed components therefor.
N.B.: SEE ALSO 9A011 AND 9A118. | M3A2 | Ramjet/scramjet/pulse jet/ ‘ combined cycle engines ’ , including devices to regulate combustion, and specially designed components therefor, usable in the systems specified in 1.A. or 19.A.2.
Technical Note: In Item 3.A.2., ‘ combined cycle engines ’ are the engines that employ two or more cycles of the following types of engines: gas-turbine engine (turbojet, turboprop, turbofan and turboshaft), ramjet, scramjet, pulse jet, pulse detonation engine, rocket motor (liquid/solid-propellant and hybrid)
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| 9A112 | “ Unmanned aerial vehicles ” ( “ UAVs ” ), other than those specified in 9A012, as follows:
a. “ Unmanned aerial vehicles ” ( “ UAVs ” ) capable of a range of 300 km;
b. “ Unmanned aerial vehicles ” ( “ UAVs ” ) having all of the following:
1. Having any of the following:
a. An autonomous flight control and navigation capability; or
b. Capability of controlled flight out of the direct vision range involving a human operator; and
2. Having any of the following:
a. Incorporating an aerosol dispensing system/mechanism with a capacity greater than 20 litres; or
b. Designed or modified to incorporate an aerosol dispensing system/mechanism with a capacity greater than 20 litres.
Technical Notes: 1. An aerosol consists of particulate or liquids other than fuel components, by products or additives, as part of the “ payload ” to be dispersed in the atmosphere. Examples of aerosols include pesticides for crop dusting and dry chemicals for cloud seeding. 2. An aerosol dispensing system/mechanism contains all those devices (mechanical, electrical, hydraulic, etc.), which are necessary for storage and dispersion of an aerosol into the atmosphere. This includes the possibility of aerosol injection into the combustion exhaust vapour and into the propeller slip stream. | M19A2 | Complete unmanned aerial vehicle systems (including cruise missile systems, target drones and reconnaissance drones), not specified in 1.A.2., capable of a “ range ” equal to or greater than 300 km. |
| M19A3 | Complete unmanned aerial vehicle systems, not specified in 1.A.2. or 19.A.2., having all of the following:
a. Having any of the following:
1. An autonomous flight control and navigation capability; or
2. Capability of controlled flight out of the direct vision range involving a human operator; and
b. Having any of the following:
1. Incorporating an aerosol dispensing system/mechanism with a capacity greater than 20 litres; or
2. Designed or modified to incorporate an aerosol dispensing system/mechanism with a capacity greater than 20 litres.
Note: Item 19.A.3. does not control model aircraft, specially designed for recreational or competition purposes. Technical Notes: 1. An aerosol consists of particulate or liquids other than fuel components, by-products or additives, as part of the “ payload ” to be dispersed in the atmosphere. Examples of aerosols include pesticides for crop dusting and dry chemicals for cloud seeding. |
| 9A115 | Launch support equipment as follows:
a. Apparatus and devices for handling, control, activation or launching, designed or modified for space launch vehicles specified in 9A004, sounding rockets specified in 9A104 or unmanned aerial vehicles specified in 9A012 or 9A112.a.;
| M12A1 | Apparatus and devices, designed or modified for the handling, control, activation and launching of the systems specified in 1.A., 19.A.1., or 19.A.2. |
b. Vehicles for transport, handling, control, activation or launching, designed or modified for space launch vehicles specified in 9A004 or sounding rockets specified in 9A104. | M12A2 | Vehicles designed or modified for the transport, handling, control, activation and launching of the systems specified in 1.A. |
| 9A116 | Reentry vehicles, usable in “ missiles ” , and equipment designed or modified therefor, as follows:
b. Heat shields and components therefor, fabricated of ceramic or ablative materials;
c. Heat sinks and components therefor, fabricated of light-weight, high heat capacity materials;
d. Electronic equipment specially designed for reentry vehicles.
| M2A1b | Re-entry vehicles, and equipment designed or modified therefor, usable in the systems specified in 1.A., as follows, except as provided in the Note below 2.A.1. for those designed for non-weapon payloads:
1. Heat shields, and components therefor, fabricated of ceramic or ablative materials;
2. Heat sinks and components therefor, fabricated of light-weight, high heat capacity materials;
3. Electronic equipment specially designed for re-entry vehicles;
|
| 9A117 | Staging mechanisms, separation mechanisms, and interstages, usable in “ missiles ” .
N.B.: SEE ALSO 9A121. | M3A4 | Staging mechanisms, separation mechanisms, and interstages therefor, usable in the systems specified in 1.A.
Note: See also Item 11.A.5. Technical Note: Staging and separation mechanisms specified in 3.A.4. may contain some of the following components:
Pyrotechnic bolts, nuts and shackles;
Ball locks;
Circular cutting devices;
Flexible linear shaped charges (FLSC).
|
| 9A118 | Devices to regulate combustion usable in engines, which are usable in “ missiles ” or unmanned aerial vehicles specified in 9A012 or 9A112.a., specified in 9A011 or 9A111. | M3A2 | Ramjet/scramjet/pulse jet/ ‘ combined cycle engines ’ , including devices to regulate combustion, and specially designed components therefor, usable in the systems specified in 1.A. or 19.A.2.
Technical Note: In Item 3.A.2., ‘ combined cycle engines ’ are the engines that employ two or more cycles of the following types of engines: gas-turbine engine (turbojet, turboprop, turbofan and turboshaft), ramjet, scramjet, pulse jet, pulse detonation engine, rocket motor (liquid/solid-propellant and hybrid).
|
| 9A119 | Individual rocket stages, usable in complete rocket systems or unmanned aerial vehicles, capable of a range of 300 km, other than those specified in 9A005, 9A007, 9A009, 9A105, 9A107 and 9A109. | M2A1a | Individual rocket stages usable in the systems specified in 1.A.; |
| M20A1a | Complete subsystems as follows: a. Individual rocket stages, not specified in 2.A.1., usable in systems specified in 19.A. |
| 9A120 | Liquid propellant tanks, other than those specified in 9A006, specially designed for propellants specified in 1C111 or ‘ other liquid propellants ’ , used in rocket systems capable of delivering at least a 500 kg payload to a range of at least 300 km. | M3A8 | Liquid propellant tanks specially designed for the propellants controlled in Item 4.C. or other liquid propellants used in the systems specified in 1.A.1. |
| 9A121 | Umbilical and interstage electrical connectors specially designed for “ missiles ” , space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.
Technical Note: Interstage connectors referred to in 9A121 also include electrical connectors installed between the “ missile ” , space launch vehicle or sounding rocket and their payload.
| M11A5 | Umbilical and interstage electrical connectors specially designed for systems specified in 1.A.1. or 19.A.1.
Technical Note: Interstage connectors referred to in 11.A.5. also include electrical connectors installed between systems specified in 1.A.1. or 19.A.1. and their “ payload ” .
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