Ek, Rob Davies, Minister van Handel en Nywerheid, kragtens artikel 13(1) van die Wet op die Nie-proliferasie van Wapens van Grootskaalse Vernietiging, 1993 (Wet No.
die onderdele tot beheerde goedere.
bepaal ek, ingevolge artikel 13(2)(f) van die Wet, dat die vervaardiging van, en verskaffing van dienste met betrekking tot, die beheerde goedere gelys in paragrawe 1, 2, 19 en 20 van die aanhangsel by hierdie kennisgewing, slegs mag plaasvind kragtens 'n permit wat deur die Raad uitgereik is.
"die Wet" die Wet op die Nie-proliferasie van Wapens van Grootskaalse Vernietiging, 1993 Wet No.
"vervaardiging" ook navorsing, ontwikkeling en fabrikasie.
'transit' is defined in the Act and should not be redefined here. Ed.
Die lys van missielverwante beheerde goedere en verwante tegnologie is vervat in die Missile Technology Control Regime (MTCR) Equipment, Software and Technology Annex, wat op 5 November 2008 bygewerk en in sy geheel in Engels aangehaal word in die aanhangsel by hierdie kennisgewing.
Goewermentskennisgewing No. 311 van 11 April 2007 word hierby herroep.
This Annex consists of two categories of items, which term includes equipment, materials, "software" or "technology". Category I items, all of which are in Annex Items 1 and 2, are those items of greatest sensitivity. If a Category I item is included in a system, that system will also be considered as Category I, except when the incorporated item cannot be separated, removed or duplicated. Category II items are those items in the Annex not designated Category I.
In reviewing the proposed applications for transfers of complete rocket and unmanned aerial vehicle systems described in Items 1 and 19, and of equipment, materials, "software" or "technology" which is listed in the Technical Annex, for potential use in such systems, the Government will take account of the ability to trade off "range" and "payload".
The transfer of "technology" directly associated with any goods controlled in the Annex is controlled according to the provisions in each Item to the extent permitted by national legislation. The approval of any Annex item for export also authorizes the export to the same end-user of the minimum "technology" required for the installation, operation, maintenance, and repair of the item.
Controls do not apply to "technology" "in the public domain" or to "basic scientific research".
"In the public domain".
The General Software Note only applies to general purpose, mass market "software".
In some instances chemicals are listed by name and CAS number. Chemicals of the same structural formula (including hydrates) are controlled regardless of name or CAS number. CAS numbers are shown to assist in identifying whether a particular chemical or mixture is controlled, irrespective of nomenclature. CAS numbers cannot be used as unique identifiers because some forms of the listed chemical have different CAS numbers, and mixtures containing a listed chemical may also have different CAS numbers.
Usually measured in terms of inaccuracy, means the maximum deviation, positive or negative, of an indicated value from an accepted standard or true value.
Experimental or theoretical work undertaken principally to acquire new knowledge of the fundamental principles of phenomena or observable facts, not primarily directed towards a specific practical aim or objective.
This means "software" or "technology" which has been made available without restrictions upon its further dissemination. Copyright restrictions do not remove "software" or "technology" from being "in the public domain".
A device in which a number of passive and/or active elements are considered as indivisibly associated on or within a continuous structure to perform the function of a circuit.
A sequence of elementary instructions maintained in a special storage, the execution of which is initiated by the introduction of its reference instruction register.
The total mass that can be carried or delivered by the specified rocket system or unmanned aerial vehicle (UAV) system that is not used to maintain flight.
The particular equipment, subsystems, or components to be included in the "payload" depends on the type and configuration of the vehicle under consideration.
Munitions of any type e.g.
Supporting structures and deployment mechanisms for the munitions e.g.
Any other countermeasures equipment e.g.
The bus/post-boost vehicle or attitude control/velocity trim module not including systems/subsystems essential to the operation of the other stages.
Munitions of any type e.g.
Any countermeasures equipment (e.g. decoys, jammers or chaff dispensers) that can be removed without violating the structural integrity of the vehicle.
Satellite-to-launch vehicle adapters including, if applicable, apogee/perigee kick motors or similar manoeuvering systems.
Recovery equipment (e.g. parachutes) that can be removed without violating the structural integrity of the vehicle.
Munitions of any type e.g.
Countermeasures equipment e.g.
Signature alteration equipment that can be removed without violating the structural integrity of the vehicle.
Munitions of any type e.g.
Countermeasures equipment e.g.
Recovery equipment (e.g. parachutes) that can be removed without violating the structural integrity of the vehicle.
Munitions supporting structures and deployment mechanisms that can be removed without violating the structural integrity of the vehicle.
Means tooling, templates, jigs, mandrels, moulds, dies, fixtures, alignment mechanisms, test equipment, other machinery and components therefor, limited to those specially designed or modified for "development" or for one or more phases of "production".
Means equipment and specially designed "software" therefor integrated into installations for "development" or for one or more phases of "production".
A sequence of instructions to carry out a process in, or convertible into, a form executable by an electronic computer.
Means that the component or equipment is designed or rated to withstand radiation levels which meet or exceed a total irradiation dose of 5 x 105 rads (Si).
The maximum distance that the specified rocket system or unmanned aerial vehicle (UAV) system is capable of travelling in the mode of stable flight as measured by the projection of its trajectory over the surface of the Earth.
The maximum capability based on the design characteristics of the system, when fully loaded with fuel or propellant, will be taken into consideration in determining "range".
The "range" for both rocket systems and UAV systems will be determined independently of any external factors such as operational restrictions, limitations imposed by telemetry, data links or other external constraints.
For rocket systems, the "range" will be determined using the trajectory that maximises "range", assuming ICAO standard atmosphere with zero wind.
For UAV systems, the "range" will be determined for a one-way distance using the most fuel-efficient flight profile (e.g. cruise speed and altitude), assuming ICAO standard atmosphere with zero wind.
A collection of one or more "programmes", or "micro-programmes", fixed in any tangible medium of expression.
Means specific information which is required for the "development", "production" or "use" of a product. The information may take the form of "technical data" or "technical assistance".
"Specially designed" describes equipment, parts, components or "software" which, as a result of "development", have unique properties that distinguish them for certain predetermined purposes. For example, a piece of equipment that is "specially designed" for use in a missile will only be considered so if it has no other function or use. Similarly, a piece of manufacturing equipment that is "specially designed" to produce a certain type of component will only be considered such if it is not capable of producing other types of components.
"Designed or modified" describes equipment, parts or components which, as a result of "development," or modification, have specified properties that make them fit for a particular application. "Designed or modified" equipment, parts, components or "software" can be used for other applications. For example, a titanium coated pump designed for a missile may be used with corrosive fluids other than propellants.
"Usable in", "usable for", "usable as" or "capable of" describes equipment, parts, components, materials or "software" which are suitable for a particular purpose. There is no need for the equipment, parts, components or "software" to have been configured, modified or specified for the particular purpose. For example, any military specification memory circuit would be "capable of" operation in a guidance system.
"Modified" in the context of "software" describes "software" which has been intentionally changed such that it has properties that make it fit for specified purposes or applications. Its properties may also make it suitable for purposes or applications other than those for which it was "modified".
1.A.1. 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.
1.A.2. 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.
1.B.1. "Production facilities" specially designed for the systems specified in 1.A.
1.D.1. "Software" specially designed or modified for the "use" of "production facilities" specified in 1.B.
1.D.2. "Software" which coordinates the function of more than one subsystem, specially designed or modified for "use" in systems specified in 1.A.
1.E.1. "Technology", in accordance with the General Technology Note, for the "development", "production" or "use" of equipment or "software" specified in 1.A., 1.B., or 1.D.
2.A.1. Complete subsystems usable in the systems specified in 1.A.
Individual rocket stages usable in the systems specified in 1.A.
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.
Solid propellant rocket motors or liquid propellant rocket engines, usable in the systems specified in 1.A., having a total impulse capacity equal to or greater than 1.
Liquid propellant apogee engines and station-keeping engines specified in 2.A.1.c., 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.
'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.
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.
´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.
Thrust vector control sub-systems, 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.
Use of thrust tabs.
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.
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.
2.B.1. "Production facilities" specially designed for the subsystems specified in 2.A.
2.B.2. "Production equipment" specially designed for the subsystems specified in 2.A.
2.D.1. "Software" specially designed or modified for the "use" of "production facilities" specified in 2.B.1.
2.D.2. "Software" specially designed or modified for the "use" of rocket motors or engines specified in 2.A.1.c.
2.D.3. "Software", specially designed or modified for the "use" of 'guidance sets' specified in 2.A.1.d.
2.D.3. includes "software", specially designed or modified to enhance the performance of ´guidance sets´ to achieve or exceed the accuracy specified in 2.A.1.d.
2.D.4. "Software" specially designed or modified for the "use" of subsystems or equipment specified in 2.A.1.b.3.
2.D.5. "Software" specially designed or modified for the "use" of systems in 2.A.1.e.
2.D.6. "Software" specially designed or modified for the "use" of systems in 2.A.1.f.
Subject to end-use statements appropriate for the excepted end-use, "software" controlled by 2.D.2. - 2.D.6.
Under 2.D.2. if specially designed or modified for liquid propellant apogee engines, designed or modified for satellite applications as specified in the Note to 2.A.1.c.
Under 2.D.5. if designed for rocket systems that do not exceed the "range" "payload" capability of systems specified in 1.A.
Under 2.D.6. if designed for systems other than those specified in 1.A.
2.E.1. "Technology", in accordance with the General Technology Note, for the "development", "production" or "use" of equipment or "software" specified in 2.A., 2.B. or 2.D.
Maximum thrust value greater than 400 N (achieved un-installed) excluding civil certified engines with a maximum thrust value greater than 8.
Specific fuel consumption of 0.
Engines designed or modified for systems specified in 1.A. or 19.A.2., regardless of thrust or specific fuel consumption.
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.
3.A.2. 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.
3.A.3. Rocket motor cases, 'insulation' components and nozzles therefor, usable in the systems specified in 1.A. or 19.A.1.
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.
Refer to 3.C.2. for ´insulation´ material in bulk or sheet form.
3.A.4. Staging mechanisms, separation mechanisms, and interstages therefor, usable in the systems specified in 1.A.
3.A.5. Liquid and slurry 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.
The only servo valves and pumps specified in 3.A.5.
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 rpm or with discharge pressures equal to or greater than 7 MPa.
Systems and components specified in 3.A.5. may be exported as part of a satellite.
3.A.6. Hybrid rocket motors and specially designed components therefor, usable in the systems specified in 1.A., 19.A.1. or 19.A.2.
c. A width between 10 and 20 mm.
3.A.8. 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.
3.A.9. '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 standard conditions), excluding civil certified engines.
For the purposes of Item 3.A.9.
b. Power transmission system to transfer the power to a propeller.
3.B.1. "Production facilities" specially designed for equipment or materials specified in 3.A.1., 3.A.2., 3.A.3., 3.A.4., 3.A.5., 3.A.6., 3.A.8., 3.A.9. or 3.C.
3.B.2. "Production equipment" specially designed for equipment or materials specified in 3.A.1., 3.A.2., 3.A.3., 3.A.4., 3.A.5., 3.A.6., 3.A.8., 3.A.9. or 3.C.
Have more than two axes which can be co-ordinated simultaneously for contouring control.
Machines combining the function of spin-forming and flow-forming are, for the purpose of this item, regarded as flow-forming machines.
This item does not include machines that are not usable in the "production" of propulsion components and equipment (e.g. motor cases) for systems specified in 1.A.
3.C.1. 'Interior lining' usable for rocket motor cases in the systems specified in 1.A. or specially designed for systems specified in 19.A.1. or 19.A.2.
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.
3.C.2. 'Insulation' material in bulk form usable for rocket motor cases in the systems specified in 1.A. or specially designed for systems specified in 19.A.1. or 19.A.2.
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.
3.D.1. "Software" specially designed or modified for the "use" of "production facilities" and flow forming machines specified in 3.B.1. or 3.B.3.
3.D.2. "Software" specially designed or modified for the "use" of equipment specified in 3.A.1., 3.A.2., 3.A.4., 3.A.5., 3.A.6. or 3.A.9.
"Software" specially designed or modified for the "use" of engines specified in 3.A.1. may be exported as part of a manned aircraft or as replacement "software" therefor.
"Software" specially designed or modified for the "use" of propellant control systems specified in 3.A.5. may be exported as part of a satellite or as replacement "software" therefor.
3.D.3. "Software" specially designed or modified for the "development" of equipment specified in 3.A.2., 3.A.3. or 3.A.4.
3.E.1. "Technology", in accordance with the General Technology Note, for the "development", "production" or "use" of equipment, materials or "software" specified in 3.A.1., 3.A.2., 3.A.3., 3.A.4., 3.A.5., 3.A.6., 3.A.9., 3.B., 3.C. or 3.D.
4.B.1. "Production equipment", and specially designed components therefor, for the "production", handling or acceptance testing of liquid propellants or propellant constituents specified in 4.C.
4.B.2. "Production equipment", other than that described in 4.B.3., and specially designed components therefor, for the production, handling, mixing, curing, casting, pressing, machining, extruding or acceptance testing of solid propellants or propellant constituents specified in 4.C.
a. Batch mixers with provision for mixing under vacuum in the range of zero to 13.
b. Continuous mixers with provision for mixing under vacuum in the range of zero to 13.
c. Fluid energy mills usable for grinding or milling substances specified in 4.C.
d. Metal powder "production equipment" usable for the "production", in a controlled environment, of spherical or atomised materials specified in 4.C.2.c., 4.C.2.d. or 4.C.2.e.
c. Equipment usable for the "production" of spherical aluminium powders by powdering a melt in an inert medium (e.g. nitrogen).
The only batch mixers, continuous mixers, usable for solid propellants or propellants constituents specified in 4.C., and fluid energy mills specified in 4.B., are those specified in 4.B.3.
Forms of metal powder "production equipment" not specified in 4.B.3.d. are to be evaluated in accordance with 4.B.2.
4.C.1. Composite and composite modified double base propellants.
A particle size of 63 µm (ISO R-565) corresponds to 250 mesh (Tyler) or 230 mesh (ASTM standard E-11).
The natural content of hafnium (CAS 7440-58-6) in the zirconium (typically 2% to 7%) is counted with the zirconium.
f. High energy density materials such as boron slurry, having an energy density of 40 x 106 J/kg or greater.
Perchlorates, chlorates or chromates mixed with powdered metals or other high energy fuel components.
Mixed Oxides of Nitrogen (MON) are solutions of Nitric Oxide (NO) in Dinitrogen Tetroxide/Nitrogen Dioxide (N2O4/NO2) that can be used in missile systems. There are a range of compositions that can be denoted as MONi or MONij where i and j are integers representing the percentage of Nitric Oxide in the mixture (e.g. MON3 contains 3% Nitric Oxide, MON25 25% Nitric Oxide. An upper limit is MON40, 40% by weight).
Item 4.C.4.a.6. does not control Nitrogen Trifluoride (NF3) (CAS 7783-54-2) in a gaseous state as it is not usable for missile applications.
f. Polytetrahydrofuran polyethylene glycol (TPEG).
Polytetrahydrofuran polyethylene glycol (TPEG) is a block co-polymer of poly 1,4-Butanediol and polyethylene glycol (PEG).
N-methyl-p-nitroaniline (CAS 100-15-2).
4.D.1. "Software" specially designed or modified for the "use" of equipment specified in 4.B. for the "production" and handling of materials specified in 4.C.
4.E.1 "Technology", in accordance with the General Technology Note, for the "development", "production" or "use" of equipment or materials specified in 4.B. and 4.C.
6.A.1. 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.
6.A.2. Resaturated pyrolised i.e.
Usable in the systems specified in 1.A. or 19.A.1.
6.B.1. Equipment for the "production" of structural composites, fibres, prepregs or preforms, usable in the systems specified in 1.A., 19.A.1. or 19.A.2.
6.B.1.c. does not control textile machinery not modified for the end-uses stated.
e. Equipment designed or modified for special fibre surface treatment or for producing prepregs and preforms, including rollers, tension stretchers, coating equipment, cutting equipment and clicker dies.
Examples of components and accessories for the machines specified in 6.B.1. are moulds, mandrels, dies, fixtures and tooling for the preform pressing, curing, casting, sintering or bonding of composite structures, laminates and manufactures thereof.
6.B.2. Nozzles specially designed for the processes referred to in 6.E.3.
c. Possessing a chamber cavity with an inside diameter of 254 mm or greater.
6.B.4. Chemical vapour deposition furnaces designed or modified for the densification of carbon-carbon composites.
6.B.5. Equipment and process controls, other than those specified in 6.B.3. or 6.B.4., designed or modified for densification and pyrolysis of structural composite rocket nozzles and re-entry vehicle nose tips.
6.C.1. Resin impregnated fibre prepregs and metal coated fibre preforms, for the goods specified in 6.A.1., made either with organic matrix or metal matrix utilising fibrous or filamentary reinforcements having a specific tensile strength greater than 7.62 x 104 m and a specific modulus greater than 3.18 x 106 m.
The only resin impregnated fibre prepregs specified in 6.C.1. are those using resins with a glass transition temperature (Tg), after cure, exceeding 145oC as determined by ASTM D4065 or national equivalents.
In Item 6.C.1. 'specific tensile strength' is the ultimate tensile strength in N/m2 divided by the specific weight in N/m3, measured at a temperature of (296 ± 2)K ((23 ± 2)°C) and a relative humidity of (50 ± 5)%.
In Item 6.C.1. 'specific modulus' is the Young's modulus in N/m2 divided by the specific weight in N/m3, measured at a temperature of (296 ± 2)K ((23 ± 2)°C) and a relative humidity of (50 ± 5)%.
6.C.2. Resaturated pyrolised i.e.
Usable in the systems specified in 1.A. or 19.A.1.
6.C.3. Fine grain graphites with a bulk density of at least 1.
Blocks having a size of 120 mm x 120 mm x 50 mm or greater.
6.C.4. Pyrolytic or fibrous reinforced graphites usable for rocket nozzles and re-entry vehicle nose tips usable in systems specified in 1.A. or 19.A.1.
6.C.5. Ceramic composite materials (dielectric constant less than 6 at any frequency from 100 MHz to 100 GHz) for use in missile radomes usable in systems specified in 1.A. or 19.A.1.
Bulk machinable silicon-carbide reinforced unfired ceramic usable for nose tips usable in systems specified in 1.A. or 19.A.1.
Reinforced silicon-carbide ceramic composites usable for nose tips, re-entry vehicles, nozzle flaps, usable in systems specified in 1.A. or 19.A.1.
6.C.7. Tungsten, molybdenum, and alloys of these metals in the form of uniform spherical or atomised particles of 500 x 10-6 m (500 µm) diameter or less with a purity of 97% or higher for fabrication of rocket motor components, i.e. heat shields, nozzle substrates, nozzle throats, and thrust vector control surfaces, usable in systems specified in 1.A. or 19.A.1.
6.C.8. Maraging steels having an ultimate tensile strength equal to or greater than 1.5 GPa, measured at 20oC, in the form of sheet, plate or tubing with a wall or plate thickness equal to or less than 5.0 mm usable in systems specified in 1.A. or 19.A.1.
Maraging steels are iron alloys generally characterised by high nickel, very low carbon content and use substitutional elements or precipitates to produce strengthening and age-hardening of the alloy.
6.C.9. Titanium-stabilized duplex stainless steel (Ti-DSS) usable in the systems specified in 1.A. or 19.A.1.
Containing 17.0 - 23.0 weight percent chromium and 4.5 - 7.
Having a titanium content of greater than 0.
Tubes having an outer diameter of 600 mm or more and a wall thickness of 3 mm or less.
6.D.1. "Software" specially designed or modified for the "use" of equipment specified in 6.B.1.
6.D.2. "Software" specially designed or modified for the equipment specified in 6.B.3., 6.B.4. or 6.B.5.
6.E.1. "Technology", in accordance with the General Technology Note, for the "development", "production" or "use" of equipment, materials or "software" specified in 6.A., 6.B., 6.C. or 6.D.
6.E.2. "Technical data" (including processing conditions) and procedures for the regulation of temperature, pressures or atmosphere in autoclaves or hydroclaves when used for the production of composites or partially processed composites, usable for equipment or materials specified in 6.A. or 6.C.
6.E.3. "Technology" for producing pyrolytically derived materials formed on a mould, mandrel or other substrate from precursor gases which decompose in the 1,300oC to 2,900oC temperature range at pressures of 130 Pa (1 mm Hg) to 20 kPa (150 mm Hg) including "technology" for the composition of precursor gases, flow-rates, and process control schedules and parameters.
9.A.1. Integrated flight instrument systems which include gyrostabilisers or automatic pilots, designed or modified for use in the systems specified in 1.A., or 19.A.1. or 19.A.2. and specially designed components therefor.
9.A.2. Gyro-astro compasses and other devices which derive position or orientation by means of automatically tracking celestial bodies or satellites, and specially designed components therefor.
9.A.3. Linear accelerometers, designed for use in inertial navigation systems or in guidance systems of all types, usable in the systems specified in 1.A., 19.A.1. or 19.A.2.
b. 'Bias' 'repeatability' less (better) than 1250 micro g.
'Bias' is defined as the accelerometer output when no acceleration is applied.
'Scale factor' is defined as the ratio of change in output to a change in the input.
The measurement of 'bias' and 'scale factor' refers to one sigma standard deviation with respect to a fixed calibration over a period of one year.
'The closeness of agreement among repeated measurements of the same variable under the same operating conditions when changes in conditions or non-operating periods occur between measurements'.
Item 9.A.3. does not control accelerometers specially designed and developed as Measurement While Drilling (MWD) sensors for use in downhole well service operations.
9.A.4. All types of gyros usable in the systems specified in 1.A., 19.A.1 or 19.A.2., with a rated 'drift rate' 'stability' of less than 0.5 degrees (1 sigma or rms) per hour in a 1 g environment, and specially designed components therefor.
'Drift rate' is defined as the component of gyro output that is functionally independent of input rotation and is expressed as an angular rate. IEEE STD 528-2001 paragraph 2.
'Stability' is defined as a measure of the ability of a specific mechanism or performance coefficient to remain invariant when continuously exposed to a fixed operating condition. (This definition does not refer to dynamic or servo stability.) (IEEE STD 528-2001 paragraph 2.
9.A.5. Accelerometers or gyros of any type, designed for use in inertial navigation systems or in guidance systems of all types, specified to function at acceleration levels greater than 100 g, and specially designed components therefor.
vibration or shock.
9.A.6. 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.
9.A.7. 'Integrated navigation systems', designed or modified for the systems specified in 1.A., 19.A.1. or 19.A.2. and capable of providing a navigational accuracy of 200 m CEP or less.
An inertial measurement device e.g.
One or more external sensors used to update the position and/or velocity, either periodically or continuously throughout the flight e.g.
c. Integration hardware and software.
N.B. For integration "software", see Item 9.D.4.
a. Internal tilt compensation in pitch (+/- 90 degrees) and having roll (+/- 180 degrees) axes.
b. Capable of providing azimuthal accuracy better (less) than 0.
c. Designed or modified to be integrated with flight control and navigation systems.
Flight control and navigation systems in Item 9.A.8. include gyrostabilisers, automatic pilots and inertial navigation systems.
9.B.1. "Production equipment", and other test, calibration and alignment equipment, other than that described in 9.B.2., designed or modified to be used with equipment specified in 9.A.
Equipment specified in 9.B.1.
Accelerometer Test Station.
Capable of balancing to a residual specific unbalance of 0.
b. Indicator heads (sometimes known as balancing instrumentation) designed or modified for use with machines specified in 9.B.2.a.
A rate resolution equal to or less than 6 degrees/s and an accuracy equal to or less than 0.
b. Having a worst-case rate stability equal to or better (less) than plus or minus 0.
e. Centrifuges capable of imparting accelerations above 100 g and designed or modified to incorporate sliprings or integrated non-contact devices capable of transferring electrical power, signal information, or both.
The only balancing machines, indicator heads, motion simulators, rate tables, positioning tables and centrifuges specified in Item 9 are those specified in 9.B.2.
9.B.2.a. does not control balancing machines designed or modified for dental or other medical equipment.
9.B.2.c. and 9.B.2.d. do not control rotary tables designed or modified for machine tools or for medical equipment.
Rate tables not controlled by 9.B.2.c. and providing the characteristics of a positioning table are to be evaluated according to 9.B.2.d.
Equipment that has the characteristics specified in 9.B.2.d. which also meets the characteristics of 9.B.2.c. will be treated as equipment specified in 9.B.2.c.
Item 9.B.2.c. applies whether or not sliprings or integrated non-contact devices are fitted at the time of export.
Item 9.B.2.e. applies whether or not sliprings or integrated non-contact devices are fitted at the time of export.
9.D.1. "Software" specially designed or modified for the "use" of equipment specified in 9.A. or 9.B.
9.D.2. Integration "software" for the equipment specified in 9.A.1.
9.D.3. Integration "software" specially designed for the equipment specified in 9.A.6.
systems' specified in 9.A.7.
A common form of integration "software" employs Kalman filtering.
9.E.1. "Technology", in accordance with the General Technology Note, for the "development", "production" or "use" of equipment or "software" specified in 9.A., 9.B. or 9.D.
Equipment or "software" specified in 9.A. or 9.D. may be exported as part of a manned aircraft, satellite, land vehicle, marine/submarine vessel or geophysical survey equipment or in quantities appropriate for replacement parts for such applications.
10.A.1. Hydraulic, mechanical, electro-optical, or electromechanical flight control systems (including fly-by-wire systems) designed or modified for the systems specified in 1.A.
10.A.2. Attitude control equipment designed or modified for the systems specified in 1.A.
10.A.3. Flight control servo valves designed or modified for the systems in 10.A.1. or 10.A.2., and designed or modified to operate in a vibration environment greater than 10 g rms between 20 Hz and 2 kHz.
Systems, equipment or valves specified in 10.A. may be exported as part of a manned aircraft or satellite or in quantities appropriate for replacement parts for manned aircraft.
10.B.1. Test, calibration, and alignment equipment specially designed for equipment specified in 10.A.
10.D.1. "Software" specially designed or modified for the "use" of equipment specified in 10.A. or 10.B.
"Software" specified in 10.D.1. may be exported as part of a manned aircraft or satellite or in quantities appropriate for replacement parts for manned aircraft.
10.E.1. Design "technology" for integration of air vehicle fuselage, propulsion system and lifting control surfaces, designed or modified for the systems specified in 1.A. or 19.A.2., to optimise aerodynamic performance throughout the flight regime of an unmanned aerial vehicle.
10.E.2. Design "technology" for integration of the flight control, guidance, and propulsion data into a flight management system, designed or modified for the systems specified in 1.A. or 19.A.1., for optimisation of rocket system trajectory.
10.E.3. "Technology", in accordance with the General Technology Note, for the "development", "production" or "use" of equipment or "software" specified in 10.A., 10.B. or 10.D.
11.A.1. Radar and laser radar systems, including altimeters, designed or modified for use in the systems specified in 1.A.
Laser radar systems embody specialised transmission, scanning, receiving and signal processing techniques for utilisation of lasers for echo ranging, direction finding and discrimination of targets by location, radial speed and body reflection characteristics.
11.A.2. Passive sensors for determining bearings to specific electromagnetic sources (direction finding equipment) or terrain characteristics, designed or modified for use in the systems specified in 1.A.
11.A.3. Receiving equipment for Global Navigation Satellite Systems GNSS; e.g.
a. Designed or modified for use in systems specified in 1.A.
Being specially designed to employ anti-jam features (e.g. null steering antenna or electronically steerable antenna) to function in an environment of active or passive countermeasures.
11.A.3.b.2. and 11.A.3.b.3. do not control equipment designed for commercial, civil or 'Safety of Life' (e.g. data integrity, flight safety) GNSS services.
11.A.4. Electronic assemblies and components, designed or modified for use in the systems specified in 1.A. or 19.A. and specially designed for military use and operation at temperatures in excess of 125oC.
Equipment specified in 11.A.
e. Imaging sensor equipment (both active and passive).
Equipment specified in 11.A. may be exported as part of a manned aircraft or satellite or in quantities appropriate for replacement parts for manned aircraft.
11.D.1. "Software" specially designed or modified for the "use" of equipment specified in 11.A.1., 11.A.2. or 11.A.4.
11.D.2. "Software" specially designed for the "use" of equipment specified in 11.A.3.
c. Design "technology" for determination of hardening criteria for the above.
11.E.2. "Technology", in accordance with the General Technology Note, for the "development", "production" or "use" of equipment or "software" specified in 11.A. or 11.D.
12.A.1. 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.
12.A.2. Vehicles designed or modified for the transport, handling, control, activation and launching of the systems specified in 1.A.
12.A.3. Gravity meters (gravimeters), gravity gradiometers, and specially designed components therefor, designed or modified for airborne or marine use, and having a static or operational accuracy of 7 x 10-6 m/s2 (0.7 milligal) or better, with a time to steady-state registration of two minutes or less, usable for systems specified in 1.A.
12.A.4. Telemetry and telecontrol equipment, including ground equipment, designed or modified for systems specified in 1.A., 19.A.1. or 19.A.2.
12.A.4. does not control equipment designed or modified for manned aircraft or satellites.
12.A.4. does not control ground based equipment designed or modified for terrestrial or marine applications.
12.A.4. does not control equipment designed for commercial, civil or 'Safety of Life' (e.g. data integrity, flight safety) GNSS services.
12.A.5. Precision tracking systems, usable for systems specified in 1.A., 19.A.1. or 19.A.2.
Angular resolution better than 1.
Velocity resolution better than 3 m/s.
12.A.6. Thermal batteries designed or modified for the systems specified in 1.A., 19.A.1. or 19.A.2.
Thermal batteries are single use batteries that contain a solid non-conducting inorganic salt as the electrolyte. These batteries incorporate a pyrolytic material that, when ignited, melts the electrolyte and activates the battery.
Item 12.A.6. does not control thermal batteries specially designed for rocket systems or unmanned aerial vehicles that are not capable of a "range" equal to or greater than 300 km.
12.D.1. "Software" specially designed or modified for the "use" of equipment specified in 12.A.1.
12.D.2. "Software" which processes post-flight, recorded data, enabling determination of vehicle position throughout its flight path, specially designed or modified for systems specified in 1.A., 19.A.1. or 19.A.2.
12.D.3. "Software" specially designed or modified for the "use" of equipment specified in 12.A.4. or 12.A.5., usable for systems specified in 1.A., 19.A.1. or 19.A.2.
12.E.1. "Technology", in accordance with the General Technology Note, for the "development", "production" or "use" of equipment or "software" specified in 12.A. or 12.D.
13.A.1. Analogue computers, digital computers or digital differential analysers, designed or modified for use in the systems specified in 1.A.
b. Designed as ruggedised or "radiation hardened".
13.E.1. "Technology", in accordance with the General Technology Note, for the "development", "production" or "use" of equipment specified in 13.A.
Item 13. equipment may be exported as part of a manned aircraft or satellite or in quantities appropriate for replacement parts for manned aircraft.
14.A.1. Analogue-to-digital converters, usable in the systems specified in 1.A.
c. Incorporating "microcircuits" specified in 14.A.1.b.1.
14.E.1. "Technology", in accordance with the General Technology Note, for the "development", "production" or "use" of equipment specified in 14.A.
15.B.1. Vibration test equipment, usable for the systems specified in 1.A., 19.A.1. or 19.A.2. or the subsystems specified in 2.A. or 20.A.
b Digital controllers, combined with specially designed vibration test "software", with a 'real-time control bandwidth' greater than 5 kHz and designed for use with vibration test systems specified in 15.B.1.a.
'Real-time control bandwidth' is defined as the maximum rate at which a controller can execute complete cycles of sampling, processing data and transmitting control signals.
c. Vibration thrusters (shaker units), with or without associated amplifiers, capable of imparting a force equal to or greater than 50 kN, measured 'bare table', and usable in vibration test systems specified in 15.B.1.a.
d. Test piece support structures and electronic units designed to combine multiple shaker units into a complete shaker system capable of providing an effective combined force equal to or greater than 50 kN, measured 'bare table', and usable in vibration test systems specified in 15.B.1.a.
Vibration test systems incorporating a digital controller are those systems, the functions of which are, partly or entirely, automatically controlled by stored and digitally coded electrical signals.
15.B.2. Wind-tunnels for speeds of Mach 0.9 or more, usable for the systems specified in 1.A. or 19.A. or the subsystems specified in 2.A. or 20.A.
15.B.3. Test benches/stands, usable for the systems specified in 1.A., 19.A.1. or 19.A.2. or the subsystems specified in 2.A. or 20.A., which have the capacity to handle solid or liquid propellant rockets, motors or engines having a thrust greater than 68 kN, or which are capable of simultaneously measuring the three axial thrust components.
15.B.4. Environmental chambers as follows, usable for the systems specified in 1.A. or 19.A. or the subsystems specified in 2.A. or 20.A.
Item 15.B.4.a.2. describes systems that are capable of generating a vibration environment with a single wave (e.g. a sine wave) and systems capable of generating a broad band random vibration (i.e. power spectrum).
In Item 15.B.4.a.2., designed or modified means the environmental chamber provides appropriate interfaces (e.g. sealing devices) to incorporate a shaker unit or other vibration test equipment as specified in this Item.
Temperature range from below -50oC to above 125oC.
15.B.5. Accelerators capable of delivering electromagnetic radiation produced by bremsstrahlung from accelerated electrons of 2 MeV or greater, and equipment containing those accelerators, usable for the systems specified in 1.A., 19.A.1. or 19.A.2. or the subsystems specified in 2.A. or 20.A.
15.B.5. does not control equipment specially designed for medical purposes.
In Item 15.B. 'bare table' means a flat table, or surface, with no fixture or fittings.
15.D.1. "Software" specially designed or modified for the "use" of equipment specified in 15.B. usable for testing systems specified in 1.A., 19.A.1. or 19.A.2. or subsystems specified in 2.A. or 20.A.
15.E.1. "Technology", in accordance with the General Technology Note, for the "development", "production" or "use" of equipment or "software" specified in 15.B. or 15.D.
16.A.1. Specially designed hybrid (combined analogue/digital) computers for modelling, simulation or design integration of systems specified in 1.A. or the subsystems specified in 2.A.
This control only applies when the equipment is supplied with "software" specified in 16.D.1.
16.D.1. "Software" specially designed for modelling, simulation, or design integration of the systems specified in 1.A. or the subsystems specified in 2.A or 20.A.
The modelling includes in particular the aerodynamic and thermodynamic analysis of the systems.
16.E.1. "Technology", in accordance with the General Technology Note, for the "development", "production" or "use" of equipment or "software" specified in 16.A. or 16.D.
17.A.1. Devices for reduced observables such as radar reflectivity, ultraviolet/infrared signatures and acoustic signatures (i.e. stealth technology), for applications usable for the systems specified in 1.A. or 19.A. or the subsystems specified in 2.A. or 20.A.
17.B.1. Systems, specially designed for radar cross section measurement, usable for the systems specified in 1.A., 19.A.1. or 19.A.2. or the subsystems specified in 2.A.
17.C.1. Materials for reduced observables such as radar reflectivity, ultraviolet/infrared signatures and acoustic signatures (i.e. stealth technology), for applications usable for the systems specified in 1.A. or 19.A. or the subsystems specified in 2.A.
17.C.1. includes structural materials and coatings (including paints), specially designed for reduced or tailored reflectivity or emissivity in the microwave, infrared or ultraviolet spectra.
17.C.1. does not control coatings (including paints) when specially used for thermal control of satellites.
17.D.1. "Software" specially designed for reduced observables such as radar reflectivity, ultraviolet/infrared signatures and acoustic signatures (i.e. stealth technology), for applications usable for the systems specified in 1.A. or 19.A. or the subsystems specified in 2.A.
17.D.1. includes "software" specially designed for analysis of signature reduction.
17.E.1. "Technology", in accordance with the General Technology Note, for the "development", "production" or "use" of equipment, materials or "software" specified in 17.A., 17.B., 17.C. or 17.D.
17.E.1. includes databases specially designed for analysis of signature reduction.
18.A.1. "Radiation Hardened" "microcircuits" usable in protecting rocket systems and unmanned aerial vehicles against nuclear effects (e.g. Electromagnetic Pulse (EMP), X-rays, combined blast and thermal effects), and usable for the systems specified in 1.A.
18.A.2. 'Detectors' specially designed or modified to protect rocket systems and unmanned aerial vehicles against nuclear effects (e.g. Electromagnetic Pulse (EMP), X-rays, combined blast and thermal effects), and usable for the systems specified in 1.A.
A ´detector´ is defined as a mechanical, electrical, optical or chemical device that automatically identifies and records, or registers a stimulus such as an environmental change in pressure or temperature, an electrical or electromagnetic signal or radiation from a radioactive material. This includes devices that sense by one time operation or failure.
18.A.3. Radomes designed to withstand a combined thermal shock greater than 4.184 x 106 J/m2 accompanied by a peak over pressure of greater than 50 kPa, usable in protecting rocket systems and unmanned aerial vehicles against nuclear effects (e.g. Electromagnetic Pulse (EMP), X-rays, combined blast and thermal effects), and usable for the systems specified in 1.A.
18.E.1. "Technology", in accordance with the General Technology Note, for the "development", "production" or "use" of equipment specified in 18.A.
19.A.1. 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.
19.A.2. 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.
19.A.3. Complete unmanned aerial vehicle systems, not specified in 1.A.2. or 19.A.2.
Designed or modified to incorporate an aerosol dispensing system/mechanism with a capacity greater than 20 litres.
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.
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.
Item 19.A.3. does not control model aircraft, specially designed for recreational or competition purposes.
19.D.1. "Software" which coordinates the function of more than one subsystem, specially designed or modified for "use" in the systems specified in 19.A.1. or 19.A.2.
19.E.1. "Technology", in accordance with the General Technology Note, for the "development", "production" or "use" of equipment specified in 19.A. 1. or 19.A.2.
a. Individual rocket stages, not specified in 2.A.1., usable in systems specified in 19.A.
b. Solid propellant rocket motors or liquid propellant rocket engines, not specified in 2.A.1., usable in systems specified in 19.A., having a total impulse capacity equal to or greater than 8.41 x 105 Ns, but less than 1.1 x 106 Ns.
20.B.1. "Production facilities" specially designed for the subsystems specified in 20.A.
20.B.2. "Production equipment" specially designed for the subsystems specified in 20.A.
20.D.1. "Software" specially designed or modified for the systems specified in 20.B.1.
20.D.2. "Software", not specified in 2.D.2., specially designed or modified for the "use" of rocket motors or engines specified in 20.A.1.b.
20.E.1. "Technology", in accordance with the General Technology Note, for the "development", "production" or "use" of equipment or "software" specified in 20.A., 20.B. or 20.D.
Global Navigation Satellite System e.g.
1 mrad ≈ 0.
1 rad (Si) = 100 ergs/gram of silicon (= 0.
for a Tyler 250 mesh, mesh opening 0.