[9A001] Aero gas turbine engines having any of the following:
Incorporating any of the "technologies" specified in 9E003.a., 9E003.h. or 9E003.i.; or
Certified by the civil aviation authorities of one or more EU Member States or Wassenaar Arrangement Participating States; and
Intended to power non-military manned "aircraft" for which any of the following has been issued by civil aviation authorities of one or more EU Member States or Wassenaar Arrangement Participating States for the "aircraft" with this specific engine type:
A civil type certificate; or
An equivalent document recognized by the International Civil Aviation Organisation (ICAO).
Designed to power an "aircraft" to cruise at Mach 1 or higher, for more than thirty minutes.
[9A002] ‘Marine gas turbine engines’ designed to use liquid fuel and having all of the following, and specially designed assemblies and components therefor:
Maximum continuous power when operating in "steady state mode" at standard reference conditions specified by ISO 3977-2:1997 (or national equivalent) of 24 245 kW or more; and
‘Corrected specific fuel consumption’ not exceeding 0,219 kg/kWh at 35 % of the maximum continuous power when using liquid fuel.
For the purposes of 9A002, ‘corrected specific fuel consumption’ is the specific fuel consumption of the engine corrected to a marine distillate liquid fuel having a net specific energy (i.e. net heating value) of 42MJ/kg (ISO 3977-2:1997).
[9A003] Specially designed assemblies or components, incorporating any of the "technologies" specified in 9E003.a., 9E003.h. or 9E003.i., for any of the following aero gas turbine engines:
Specified in 9A001; or
Whose design or production origins are either non-EU Member States or Wassenaar Arrangement Participating States or unknown to the manufacturer.
[9A004] Space launch vehicles, "spacecraft", "spacecraft buses", "spacecraft payloads", "spacecraft" on-board systems or equipment, terrestrial equipment, and air-launch platforms as follows:
Space launch vehicles;
"Spacecraft";
"Spacecraft buses";
"Spacecraft payloads" incorporating items specified in 3A001.b.1.a.4., 3A002.g., 5A001.a.1., 5A001.b.3., 5A002.c., 5A002.e., 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.;
On-board systems or equipment, specially designed for "spacecraft" and having any of the following functions:
‘Command and telemetry data handling’;
Terrestrial equipment specially designed for "spacecraft", as follows:
Telemetry and telecommand equipment specially designed for any of the following data processing functions:
Telemetry data processing of frame synchronisation and error corrections, for monitoring of operational status (also known as health and safe status) of the "spacecraft bus"; or
Command data processing for formatting command data being sent to the "spacecraft" to control the "spacecraft bus";
Simulators specially designed for ‘verification of operational procedures’ of "spacecraft";
For the purposes of 9A004.f.2., ‘verification of operational procedures’ is any of the following:
"Aircraft" specially designed or modified to be air-launch platforms for space launch vehicles;
"Sub-orbital craft".
[9A005] Liquid rocket propulsion systems containing any of the systems or components, specified in 9A006.
[9A006] Systems and components, specially designed for liquid rocket propulsion systems, as follows:
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;
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";
Slush hydrogen storage or transfer systems;
High pressure (exceeding 17,5 MPa) turbo pumps, pump components or their associated gas generator or expander cycle turbine drive systems;
High-pressure (exceeding 10,6 MPa) thrust chambers and nozzles therefor;
Propellant storage systems using the principle of capillary containment or positive expulsion (i.e., with flexible bladders);
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;
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.
[9A007] Solid rocket propulsion systems having any of the following:
Total impulse capacity exceeding 1,1 MNs;
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;
Stage mass fractions exceeding 88 % and propellant solid loadings exceeding 86 %;
Components specified in 9A008; or
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.
‘Strong mechanical bond’ means bond strength equal to or more than propellant strength.
[9A008] Components specially designed for solid rocket propulsion systems, as follows:
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;
‘Strong mechanical bond’ means bond strength equal to or more than propellant strength.
Filament-wound "composite" motor cases exceeding 0,61 m in diameter or having ‘structural efficiency ratios (PV/W)’ exceeding 25 km;
‘Structural efficiency ratio (PV/W)’ is the burst pressure (P) multiplied by the vessel volume (V) divided by the total pressure vessel weight (W).
Nozzles with thrust levels exceeding 45 kN or nozzle throat erosion rates of less than 0,075 mm/s;
Movable nozzle or secondary fluid injection thrust vector control systems, capable of any of the following:
Omni-axial movement exceeding ± 5°;
Angular vector rotations of 20°/s or more; or
Angular vector accelerations of 40°/s2 or more.
[9A009] Hybrid rocket propulsion systems having any of the following:
Total impulse capacity exceeding 1,1 MNs; or
Thrust levels exceeding 220 kN in vacuum exit conditions.
[9A010] Specially designed components, systems and structures, for launch vehicles, launch vehicle propulsion systems or "spacecraft", as follows:
Components and structures, each exceeding 10 kg and specially designed for launch vehicles manufactured using any of the following:
"Composite" materials consisting of "fibrous or filamentary materials" specified in 1C010.e. and resins specified in 1C008 or 1C009.b.;
Metal "matrix""composites" reinforced by any of the following:
Materials specified in 1C007;
"Fibrous or filamentary materials" specified in 1C010; or
Aluminides specified in 1C002.a.; or
Components and structures, specially designed for launch vehicle propulsion systems specified in 9A005 to 9A009 manufactured using any of the following:
"Fibrous or filamentary materials" specified in 1C010.e. and resins specified in 1C008 or 1C009.b.;
Metal "matrix""composites" reinforced by any of the following:
Materials specified in 1C007;
"Fibrous or filamentary materials" specified in 1C010; or
Aluminides specified in 1C002.a.; or
Ceramic "matrix""composite" materials specified in 1C007;
Structural components and isolation systems, specially designed to control actively the dynamic response or distortion of "spacecraft" structures;
[9A011] Ramjet, scramjet or ‘combined cycle engines’, and specially designed components therefor.
For the purposes of 9A011, ‘combined cycle engines’ combine two or more of the following types of engines: U.K.
Gas turbine engine (turbojet, turboprop and turbofan);
Ramjet or scramjet;
Rocket motor or engine (liquid/gel/solid-propellant and hybrid).
[9A012] "Unmanned aerial vehicles" ("UAVs"), unmanned "airships", related equipment and components, as follows:
"UAVs" or unmanned "airships", designed to have controlled flight out of the direct ‘natural vision’ of the ‘operator’ and having any of the following:
Having all of the following:
A maximum ‘endurance’ greater than or equal to 30 minutes but less than 1 hour; and
Designed to take-off and have stable controlled flight in wind gusts equal to or exceeding 46,3 km/h (25 knots); or
A maximum ‘endurance’ of 1 hour or greater;
Related equipment and components, as follows:
Not used;
Not used;
Equipment or components, specially designed to convert a manned "aircraft" or manned "airship", to a "UAV" or unmanned "airship", specified in 9A012.a.;
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).
[9A101] Turbojet and turbofan engines, other than those specified in 9A001, as follows;
Engines having all of the following characteristics:
‘Maximum thrust value’ greater than 400 N excluding civil certified engines with a ‘maximum thrust value’ greater than 8 890 N;
Specific fuel consumption of 0,15 kg N–1 h–1 or less;
‘Dry weight’ less than 750 kg; and
‘First-stage rotor diameter’ less than 1 m;
Engines designed or modified for use in "missiles" or unmanned aerial vehicles specified in 9A012 or 9A112.a.
[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.
Turboshaft engine; and
Power transmission system to transfer the power to a propeller.
[9A104] Sounding rockets, capable of a range of at least 300 km.
[9A105] Liquid propellant rocket engines or gel propellant rocket motors, as follows:
Liquid propellant rocket engines or gel propellant rocket motors, usable in "missiles", other than those specified in 9A005, 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 MNs;
Liquid propellant rocket engines or gel propellant rocket motors, 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 or gel propellant propulsion system which has a total impulse capacity equal to or greater than 0,841 MNs.
[9A106] Systems or components, other than those specified in 9A006 as follows, specially designed for liquid rocket propulsion or gel propellant rocket systems:
Not used;
Not used;
Thrust vector control sub-systems, usable in "missiles";
Examples of methods of achieving thrust vector control specified in 9A106.c. are: U.K.
Flexible nozzle;
Fluid or secondary gas injection;
Movable engine or nozzle;
Deflection of exhaust gas stream (jet vanes or probes); or
Thrust tabs.
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;
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;
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;
Gas turbines, for liquid propellant turbopumps, with shaft speeds equal to or greater than 8 000 r.p.m. at the maximum operating mode.
Combustion chambers and nozzles for liquid propellant rocket engines or gel propellant rocket motors specified in 9A005 or 9A105.
[9A107] Solid propellant rocket motors, 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.
[9A108] Components, other than those specified in 9A008, as follows, specially designed for solid and hybrid rocket propulsion systems:
Rocket motor cases and "insulation" components therefor, usable in subsystems specified in 9A007, 9A009, 9A107 or 9A109.a.;
Rocket nozzles, usable in subsystems specified in 9A007, 9A009, 9A107 or 9A109.a.;
Thrust vector control sub-systems, usable in "missiles".
Examples of methods of achieving thrust vector control specified in 9A108.c. are:
Flexible nozzle;
Fluid or secondary gas injection;
Movable engine or nozzle;
Deflection of exhaust gas stream (jet vanes or probes); or
Thrust tabs.
[9A109] Hybrid rocket motors and specially designed components as follows:
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;
Specially designed components for hybrid rocket motors specified in 9A009 that are usable in "missiles".
[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.
In 9A110 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.
[9A111] Pulse jet or detonation engines, usable in "missiles" or unmanned aerial vehicles specified in 9A012 or 9A112.a., and specially designed components therefor.
In 9A111 detonation engines utilise detonation to produce a rise in effective pressure across the combustion chamber. Examples of detonation engines include pulse detonation engines, rotating detonation engines or continuous wave detonation engines.
[9A112] "Unmanned aerial vehicles" ("UAVs"), other than those specified in 9A012, as follows:
"Unmanned aerial vehicles" ("UAVs") capable of a range of 300 km;
"Unmanned aerial vehicles" ("UAVs") having all of the following:
Having any of the following:
An autonomous flight control and navigation capability; or
Capability of controlled flight out of the direct vision range involving a human operator; and
Having any of the following:
Incorporating an aerosol dispensing system/mechanism with a capacity greater than 20 litres; or
Designed or modified to incorporate an aerosol dispensing system/mechanism with a capacity greater than 20 litres.
[9A115] Launch support equipment as follows:
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 ‘missiles’;
In 9A115.a. ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.
Vehicles for transport, handling, control, activation or launching, designed or modified for space launch vehicles specified in 9A004, sounding rockets specified in 9A104 or "missiles".
[9A116] Reentry vehicles, usable in "missiles", and equipment designed or modified therefor, as follows:
Reentry vehicles;
Heat shields and components therefor, fabricated of ceramic or ablative materials;
Heat sinks and components therefor, fabricated of light-weight, high heat capacity materials;
Electronic equipment specially designed for reentry vehicles.
[9A117] Staging mechanisms, separation mechanisms, and interstages, usable in "missiles".
[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.
[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.
[9A120] Liquid or gel propellant tanks, other than those specified in 9A006, specially designed for propellants specified in 1C111 or ‘other liquid or gel propellants’ used in rocket systems capable of delivering at least a 500 kg payload to a range of at least 300 km.
[9A121] Umbilical and interstage electrical connectors specially designed for "missiles", space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.
Interstage connectors referred to in 9A121 also include electrical connectors installed between the "missile", space launch vehicle or sounding rocket and their payload.
[9A350] Spraying or fogging systems, specially designed or modified for fitting to aircraft, "lighter-than-air vehicles" or unmanned aerial vehicles, and specially designed components therefor, as follows:
Complete spraying or fogging systems capable of delivering, from a liquid suspension, an initial droplet ‘VMD’ of less than 50 μm at a flow rate of greater than two litres per minute;
Spray booms or arrays of aerosol generating units capable of delivering, from a liquid suspension, an initial droplet ‘VMD’ of less than 50 μm at a flow rate of greater than two litres per minute;
Doppler laser method;
Forward laser diffraction method.