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“Guidance sets”, usable in “missiles” 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).
Authority: EUProhibited Supply To: IRProgram: IREU Code: M2A1dCode: 7A117“Guidance sets”, usable in “missiles” 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).
Authority: EUProhibited Supply To: IRProgram: IREU Code: M2A1dCode: 7A117c. Flight control servo valves designed or modified for the systems specified in 7A116.a. or 7A116.b., and designed or modified to operate in a vibration environment greater than 10 g rms between 20 Hz and 2 kHz.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M10A3Code: 7A116c. Flight control servo valves designed or modified for the systems specified in 7A116.a. or 7A116.b., and designed or modified to operate in a vibration environment greater than 10 g rms between 20 Hz and 2 kHz.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M10A3Code: 7A116b. Attitude control equipment;
Authority: EUProhibited Supply To: IRProgram: IREU Code: M10A2Code: 7A116b. Attitude control equipment;
Authority: EUProhibited Supply To: IRProgram: IREU Code: M10A2Code: 7A116Flight control systems and servo valves, as follows; designed or modified for use in space launch vehicles specified in 9A004 or sounding rockets specified in 9A104. a. Hydraulic, mechanical, electro-optical, or electro-mechanical flight control systems (including fly-by-wire types);
Authority: EUProhibited Supply To: IRProgram: IREU Code: M10A1Code: 7A116Flight control systems and servo valves, as follows; designed or modified for use in space launch vehicles specified in 9A004 or sounding rockets specified in 9A104. a. Hydraulic, mechanical, electro-optical, or electro-mechanical flight control systems (including fly-by-wire types);
Authority: EUProhibited Supply To: IRProgram: IREU Code: M10A1Code: 7A116Passive sensors for determining bearing to specific electromagnetic source (direction finding equipment) or terrain characteristics, designed or modified for use in space launch vehicles specified in 9A004 or sounding rockets specified in 9A104. Note: 7A115 includes sensors for the following equipment: a. Terrain contour mapping equipment; b. Imaging sensor equipment (both active and passive); c. Passive interferometer equipment
Authority: EUProhibited Supply To: IRProgram: IREU Code: M11A2Code: 7A115Passive sensors for determining bearing to specific electromagnetic source (direction finding equipment) or terrain characteristics, designed or modified for use in space launch vehicles specified in 9A004 or sounding rockets specified in 9A104. Note: 7A115 includes sensors for the following equipment: a. Terrain contour mapping equipment; b. Imaging sensor equipment (both active and passive); c. Passive interferometer equipment
Authority: EUProhibited Supply To: IRProgram: IREU Code: M11A2Code: 7A115Altimeters, other than those specified in 7A006, of radar or laser radar type, designed or modified for use in space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M11A1Code: 7A106Altimeters, other than those specified in 7A006, of radar or laser radar type, designed or modified for use in space launch vehicles specified in 9A004 or sounding rockets specified in 9A104.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M11A1Code: 7A106Receiving equipment for Global Navigation Satellite Systems (GNSS; e.g. GPS, GLONASS, or Galileo), other than those specified in 7A005, having any of the following characteristics, and specially designed components therefor: a. Designed or modified for use in space launch vehicles specified in 9A004, sounding rockets specified in 9A104 or unmanned aerial vehicles specified in 9A012 or 9A112.a.; or b. Designed or modified for airborne applications and having any of the following: 1. Capable of providing navigation information at speeds in excess of 600 m/s; 2. Employing decryption, designed or modified for military or governmental services, to gain access to GNSS secured signal/data; or 3. 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. Note: 7A105.b.2. and 7A105.b.3. do not control equipment designed for commercial, civil or ‘Safety of Life’ (e.g., data integrity, flight safety) GNSS services.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M11A3Code: 7A105Receiving equipment for Global Navigation Satellite Systems (GNSS; e.g. GPS, GLONASS, or Galileo), other than those specified in 7A005, having any of the following characteristics, and specially designed components therefor: a. Designed or modified for use in space launch vehicles specified in 9A004, sounding rockets specified in 9A104 or unmanned aerial vehicles specified in 9A012 or 9A112.a.; or b. Designed or modified for airborne applications and having any of the following: 1. Capable of providing navigation information at speeds in excess of 600 m/s; 2. Employing decryption, designed or modified for military or governmental services, to gain access to GNSS secured signal/data; or 3. 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. Note: 7A105.b.2. and 7A105.b.3. do not control equipment designed for commercial, civil or ‘Safety of Life’ (e.g., data integrity, flight safety) GNSS services.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M11A3Code: 7A105Gyro-astro compasses and other devices, other than those specified in 7A004, which derive position or orientation by means of automatically tracking celestial bodies or satellites and specially designed components therefor.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M9A2Code: 7A104Gyro-astro compasses and other devices, other than those specified in 7A004, which derive position or orientation by means of automatically tracking celestial bodies or satellites and specially designed components therefor.
Authority: EUProhibited Supply To: IRProgram: IREU Code: M9A2Code: 7A104d. Three axis magnetic heading sensors, designed or modified to be integrated with flight control and navigation systems, other than those specified in 6A006, having all the following characteristics, and specially designed components therefor; 1. Internal tilt compensation in pitch (± 90 degrees) and roll (± 180 degrees) axes; 2. Capable of providing azimuthal accuracy better (less) than 0,5 degrees rms at latitude of ± 80 degrees, reference to local magnetic field. Note: Flight control and navigation systems in 7A103.d. include gyrostabilizers, automatic pilots and inertial navigation systems. Technical Note: In 7A103 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M9A8Code: 7A103d. Three axis magnetic heading sensors, designed or modified to be integrated with flight control and navigation systems, other than those specified in 6A006, having all the following characteristics, and specially designed components therefor; 1. Internal tilt compensation in pitch (± 90 degrees) and roll (± 180 degrees) axes; 2. Capable of providing azimuthal accuracy better (less) than 0,5 degrees rms at latitude of ± 80 degrees, reference to local magnetic field. Note: Flight control and navigation systems in 7A103.d. include gyrostabilizers, automatic pilots and inertial navigation systems. Technical Note: In 7A103 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M9A8Code: 7A103c. ‘Integrated navigation systems’, designed or modified for ‘missiles’ and capable of providing a navigational accuracy of 200 m Circle of Equal Probability (CEP) or less; Technical Note: An ‘integrated navigation system’ typically incorporates the following components: 1. An inertial measurement device (e.g., an attitude and heading reference system, inertial reference unit, or inertial navigation system); 2. One or more external sensors used to update the position and/or velocity, either periodically or continuously throughout the flight (e.g., satellite navigation receiver, radar altimeter, and/or Doppler radar); and 3. Integration hardware and software;
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M9A7Code: 7A103c. ‘Integrated navigation systems’, designed or modified for ‘missiles’ and capable of providing a navigational accuracy of 200 m Circle of Equal Probability (CEP) or less; Technical Note: An ‘integrated navigation system’ typically incorporates the following components: 1. An inertial measurement device (e.g., an attitude and heading reference system, inertial reference unit, or inertial navigation system); 2. One or more external sensors used to update the position and/or velocity, either periodically or continuously throughout the flight (e.g., satellite navigation receiver, radar altimeter, and/or Doppler radar); and 3. Integration hardware and software;
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M9A7Code: 7A103b. Integrated flight instrument systems which include gyrostabilisers or automatic pilots, designed or modified for use in ‘missiles’;
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M9A1Code: 7A103b. Integrated flight instrument systems which include gyrostabilisers or automatic pilots, designed or modified for use in ‘missiles’;
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M9A1Code: 7A103Instrumentation, navigation equipment and systems, other than those specified in 7A003, as follows; and specially designed components therefor: a. Inertial or other equipment, using accelerometers or gyros as follows, and systems incorporating such equipment: 1. Accelerometers specified in 7A001.a.3., 7A001.b. or 7A101 or gyros specified in 7A002 or 7A102; or 2. Accelerometers specified in 7A001.a.1. or 7A001.a.2., designed for use in inertial navigation systems or in guidance systems of all types, and usable in ‘missiles’; Note: 7A103.a. does not specify equipment containing accelerometers specified in 7A001 where such accelerometers are specially designed and developed as MWD (Measurement While Drilling) sensors for use in down-hole well services operations.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M9A6Code: 7A103Instrumentation, navigation equipment and systems, other than those specified in 7A003, as follows; and specially designed components therefor: a. Inertial or other equipment, using accelerometers or gyros as follows, and systems incorporating such equipment: 1. Accelerometers specified in 7A001.a.3., 7A001.b. or 7A101 or gyros specified in 7A002 or 7A102; or 2. Accelerometers specified in 7A001.a.1. or 7A001.a.2., designed for use in inertial navigation systems or in guidance systems of all types, and usable in ‘missiles’; Note: 7A103.a. does not specify equipment containing accelerometers specified in 7A001 where such accelerometers are specially designed and developed as MWD (Measurement While Drilling) sensors for use in down-hole well services operations.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M9A6Code: 7A103All types of gyros, other than those specified in 7A002, usable in ‘missiles’, with a rated “drift rate”‘stability’ of less than 0,5° (1 sigma or rms) per hour in a 1 g environment and specially designed components therefor. Technical Notes: 1. In 7A102 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km. 2. In 7A102 ‘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 (IEEE STD 528-2001 paragraph 2.247).
Authority: EUProhibited Supply To: IRProgram: IREU Code: M9A4Code: 7A102All types of gyros, other than those specified in 7A002, usable in ‘missiles’, with a rated “drift rate”‘stability’ of less than 0,5° (1 sigma or rms) per hour in a 1 g environment and specially designed components therefor. Technical Notes: 1. In 7A102 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km. 2. In 7A102 ‘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 (IEEE STD 528-2001 paragraph 2.247).
Authority: EUProhibited Supply To: IRProgram: IREU Code: M9A4Code: 7A102Linear accelerometers, other than those specified in 7A001, designed for use in inertial navigation systems or in guidance systems of all types, usable in ‘missiles’, having all the following characteristics, and specially designed components therefor: a. A “bias”“repeatability” of less (better) than 1 250 micro g; and b. A “scale factor”“repeatability” of less (better) than 1 250 ppm; Note: 7A101 does not control accelerometers specially designed and developed as Measurement While Drilling (MWD) Sensors for use in downhole well service operations. Technical Notes: 1. In 7A101 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km; 2. In 7A101 the measurement of “bias” and “scale factor” refers to a one sigma standard deviation with respect to a fixed calibration over a period of one year;
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M9A3Code: 7A101Linear accelerometers, other than those specified in 7A001, designed for use in inertial navigation systems or in guidance systems of all types, usable in ‘missiles’, having all the following characteristics, and specially designed components therefor: a. A “bias”“repeatability” of less (better) than 1 250 micro g; and b. A “scale factor”“repeatability” of less (better) than 1 250 ppm; Note: 7A101 does not control accelerometers specially designed and developed as Measurement While Drilling (MWD) Sensors for use in downhole well service operations. Technical Notes: 1. In 7A101 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km; 2. In 7A101 the measurement of “bias” and “scale factor” refers to a one sigma standard deviation with respect to a fixed calibration over a period of one year;
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M9A3Code: 7A101Airborne altimeters operating at frequencies other than 4,2 to 4,4 GHz inclusive and having any of the following: N.B.: SEE ALSO 7A106. a. “Power management”; or b. Using phase shift key modulation.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M11A1Code: 7A006Airborne altimeters operating at frequencies other than 4,2 to 4,4 GHz inclusive and having any of the following: N.B.: SEE ALSO 7A106. a. “Power management”; or b. Using phase shift key modulation.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M11A1Code: 7A006Global Navigation Satellite Systems (GNSS) receiving equipment having any of the following and specially designed components therefor: N.B.: SEE ALSO 7A105. N.B.: For equipment specially designed for military use, see Military Goods Controls. a. Employing a decryption algorithm specially designed or modified for government use to access the ranging code for position and time; or b. Employing ‘adaptive antenna systems’. Note: 7A005.b. does not control GNSS receiving equipment that only uses components designed to filter, switch, or combine signals from multiple omni-directional antennae that do not implement adaptive antenna techniques. Technical Note: For the purposes of 7A005.b ‘adaptive antenna systems’ dynamically generate one or more spatial nulls in an antenna array pattern by signal processing in the time domain or frequency domain.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M11A3Code: 7A005Global Navigation Satellite Systems (GNSS) receiving equipment having any of the following and specially designed components therefor: N.B.: SEE ALSO 7A105. N.B.: For equipment specially designed for military use, see Military Goods Controls. a. Employing a decryption algorithm specially designed or modified for government use to access the ranging code for position and time; or b. Employing ‘adaptive antenna systems’. Note: 7A005.b. does not control GNSS receiving equipment that only uses components designed to filter, switch, or combine signals from multiple omni-directional antennae that do not implement adaptive antenna techniques. Technical Note: For the purposes of 7A005.b ‘adaptive antenna systems’ dynamically generate one or more spatial nulls in an antenna array pattern by signal processing in the time domain or frequency domain.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M11A3Code: 7A005‘Star trackers’ and components therefor, as follows: N.B.: SEE ALSO 7A104. a. ‘Star trackers’ with a specified azimuth accuracy of equal to or less (better) than 20 seconds of arc throughout the specified lifetime of the equipment; b. Components specially designed for equipment specified in 7A004.a. as follows: 1. Optical heads or baffles; 2. Data processing units. Technical Note: ‘Star trackers’ are also referred to as stellar attitude sensors or gyro-astro compasses.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M9A2Code: 7A004‘Star trackers’ and components therefor, as follows: N.B.: SEE ALSO 7A104. a. ‘Star trackers’ with a specified azimuth accuracy of equal to or less (better) than 20 seconds of arc throughout the specified lifetime of the equipment; b. Components specially designed for equipment specified in 7A004.a. as follows: 1. Optical heads or baffles; 2. Data processing units. Technical Note: ‘Star trackers’ are also referred to as stellar attitude sensors or gyro-astro compasses.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M9A2Code: 7A004‘Inertial measurement equipment or systems’, having any of the following: N.B.: SEE ALSO 7A103. Note 1: ‘Inertial measurement equipment or systems’ incorporate accelerometers or gyroscopes to measure changes in velocity and orientation in order to determine or maintain heading or position without requiring an external reference once aligned. ‘Inertial measurement equipment or systems’ include: — Attitude and Heading Reference Systems (AHRSs); — Gyrocompasses; — Inertial Measurement Units (IMUs); — Inertial Navigation Systems (INSs); — Inertial Reference Systems (IRSs); — Inertial Reference Units (IRUs). Note 2: 7A003 does not control ‘inertial measurement equipment or systems’ which are certified for use on “civil aircraft” by civil aviation authorities of one or more “participating states”. Technical Notes: 1. ‘Positional aiding references’ independently provide position, and include: a. Global Navigation Satellite Systems (GNSS); b. “Data-Based Referenced Navigation” (“DBRN”). 2. ‘Circular Error Probable’ (‘CEP’) — In a circular normal distribution, the radius of the circle containing 50 % of the individual measurements being made, or the radius of the circle within which there is a 50 % probability of being located. a. Designed for “aircraft”, land vehicles or vessels, providing position without the use of ‘positional aiding references’, and having any of the following accuracies subsequent to normal alignment: 1. 0,8 nautical miles per hour (nm/hr) ‘Circular Error Probable’ (‘CEP’) rate or less (better); 2. 0,5 % distanced travelled ‘CEP’ or less (better); or 3. Total drift of 1 nautical mile ‘CEP’ or less (better) in a 24 hr period; Technical Note: The performance parameters in 7A003.a.1., 7A003.a.2. and 7A003.a.3. typically apply to ‘inertial measurement equipment or systems’ designed for “aircraft”, vehicles and vessels, respectively. These parameters result from the utilisation of specialised non-positional aiding references (e.g., altimeter, odometer, velocity log). As a consequence, the specified performance values cannot be readily converted between these parameters. Equipment designed for multiple platforms are evaluated against each applicable entry 7A003.a.1., 7A003.a.2., or 7A003.a.3. b. Designed for “aircraft”, land vehicles or vessels, with an embedded ‘positional aiding reference’ and providing position after loss of all ‘positional aiding references’ for a period of up to 4 minutes, having an accuracy of less (better) than 10 meters ‘CEP’; Technical Note: 7A003.b. refers to systems in which ‘inertial measurement equipment or systems’ and other independent ‘positional aiding references’ are built into a single unit (i.e., embedded) in order to achieve improved performance. c. Designed for “aircraft”, land vehicles or vessels, providing heading or True North determination and having any of the following: 1. A maximum operating angular rate less (lower) than 500 deg/s and a heading accuracy without the use of ‘positional aiding references’ equal to or less (better) than 0,07 deg sec(Lat) (equivalent to 6 arc minutes rms at 45 degrees latitude); or 2. A maximum operating angular rate equal to or greater (higher) than 500 deg/s and a heading accuracy without the use of ‘positional aiding references’ equal to or less (better) than 0,2 deg sec(Lat) (equivalent to 17 arc minutes rms at 45 degrees latitude); or d. Providing acceleration measurements or angular rate measurements, in more than one dimension, and having any of the following: 1. Performance specified by 7A001 or 7A002 along any axis, without the use of any aiding references; or 2. Being “space-qualified” and providing angular rate measurements having an “angle random walk” along any axis of less (better) than or equal to 0,1 degree per square root hour. Note: 7A003.d.2. does not control ‘inertial measurement equipment or systems’ that contain “spinning mass gyros” as the only type of gyro.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M9A8Code: 7A003‘Inertial measurement equipment or systems’, having any of the following: N.B.: SEE ALSO 7A103. Note 1: ‘Inertial measurement equipment or systems’ incorporate accelerometers or gyroscopes to measure changes in velocity and orientation in order to determine or maintain heading or position without requiring an external reference once aligned. ‘Inertial measurement equipment or systems’ include: — Attitude and Heading Reference Systems (AHRSs); — Gyrocompasses; — Inertial Measurement Units (IMUs); — Inertial Navigation Systems (INSs); — Inertial Reference Systems (IRSs); — Inertial Reference Units (IRUs). Note 2: 7A003 does not control ‘inertial measurement equipment or systems’ which are certified for use on “civil aircraft” by civil aviation authorities of one or more “participating states”. Technical Notes: 1. ‘Positional aiding references’ independently provide position, and include: a. Global Navigation Satellite Systems (GNSS); b. “Data-Based Referenced Navigation” (“DBRN”). 2. ‘Circular Error Probable’ (‘CEP’) — In a circular normal distribution, the radius of the circle containing 50 % of the individual measurements being made, or the radius of the circle within which there is a 50 % probability of being located. a. Designed for “aircraft”, land vehicles or vessels, providing position without the use of ‘positional aiding references’, and having any of the following accuracies subsequent to normal alignment: 1. 0,8 nautical miles per hour (nm/hr) ‘Circular Error Probable’ (‘CEP’) rate or less (better); 2. 0,5 % distanced travelled ‘CEP’ or less (better); or 3. Total drift of 1 nautical mile ‘CEP’ or less (better) in a 24 hr period; Technical Note: The performance parameters in 7A003.a.1., 7A003.a.2. and 7A003.a.3. typically apply to ‘inertial measurement equipment or systems’ designed for “aircraft”, vehicles and vessels, respectively. These parameters result from the utilisation of specialised non-positional aiding references (e.g., altimeter, odometer, velocity log). As a consequence, the specified performance values cannot be readily converted between these parameters. Equipment designed for multiple platforms are evaluated against each applicable entry 7A003.a.1., 7A003.a.2., or 7A003.a.3. b. Designed for “aircraft”, land vehicles or vessels, with an embedded ‘positional aiding reference’ and providing position after loss of all ‘positional aiding references’ for a period of up to 4 minutes, having an accuracy of less (better) than 10 meters ‘CEP’; Technical Note: 7A003.b. refers to systems in which ‘inertial measurement equipment or systems’ and other independent ‘positional aiding references’ are built into a single unit (i.e., embedded) in order to achieve improved performance. c. Designed for “aircraft”, land vehicles or vessels, providing heading or True North determination and having any of the following: 1. A maximum operating angular rate less (lower) than 500 deg/s and a heading accuracy without the use of ‘positional aiding references’ equal to or less (better) than 0,07 deg sec(Lat) (equivalent to 6 arc minutes rms at 45 degrees latitude); or 2. A maximum operating angular rate equal to or greater (higher) than 500 deg/s and a heading accuracy without the use of ‘positional aiding references’ equal to or less (better) than 0,2 deg sec(Lat) (equivalent to 17 arc minutes rms at 45 degrees latitude); or d. Providing acceleration measurements or angular rate measurements, in more than one dimension, and having any of the following: 1. Performance specified by 7A001 or 7A002 along any axis, without the use of any aiding references; or 2. Being “space-qualified” and providing angular rate measurements having an “angle random walk” along any axis of less (better) than or equal to 0,1 degree per square root hour. Note: 7A003.d.2. does not control ‘inertial measurement equipment or systems’ that contain “spinning mass gyros” as the only type of gyro.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M9A8Code: 7A003‘Inertial measurement equipment or systems’, having any of the following: N.B.: SEE ALSO 7A103. Note 1: ‘Inertial measurement equipment or systems’ incorporate accelerometers or gyroscopes to measure changes in velocity and orientation in order to determine or maintain heading or position without requiring an external reference once aligned. ‘Inertial measurement equipment or systems’ include: — Attitude and Heading Reference Systems (AHRSs); — Gyrocompasses; — Inertial Measurement Units (IMUs); — Inertial Navigation Systems (INSs); — Inertial Reference Systems (IRSs); — Inertial Reference Units (IRUs). Note 2: 7A003 does not control ‘inertial measurement equipment or systems’ which are certified for use on “civil aircraft” by civil aviation authorities of one or more “participating states”. Technical Notes: 1. ‘Positional aiding references’ independently provide position, and include: a. Global Navigation Satellite Systems (GNSS); b. “Data-Based Referenced Navigation” (“DBRN”). 2. ‘Circular Error Probable’ (‘CEP’) — In a circular normal distribution, the radius of the circle containing 50 % of the individual measurements being made, or the radius of the circle within which there is a 50 % probability of being located. a. Designed for “aircraft”, land vehicles or vessels, providing position without the use of ‘positional aiding references’, and having any of the following accuracies subsequent to normal alignment: 1. 0,8 nautical miles per hour (nm/hr) ‘Circular Error Probable’ (‘CEP’) rate or less (better); 2. 0,5 % distanced travelled ‘CEP’ or less (better); or 3. Total drift of 1 nautical mile ‘CEP’ or less (better) in a 24 hr period; Technical Note: The performance parameters in 7A003.a.1., 7A003.a.2. and 7A003.a.3. typically apply to ‘inertial measurement equipment or systems’ designed for “aircraft”, vehicles and vessels, respectively. These parameters result from the utilisation of specialised non-positional aiding references (e.g., altimeter, odometer, velocity log). As a consequence, the specified performance values cannot be readily converted between these parameters. Equipment designed for multiple platforms are evaluated against each applicable entry 7A003.a.1., 7A003.a.2., or 7A003.a.3. b. Designed for “aircraft”, land vehicles or vessels, with an embedded ‘positional aiding reference’ and providing position after loss of all ‘positional aiding references’ for a period of up to 4 minutes, having an accuracy of less (better) than 10 meters ‘CEP’; Technical Note: 7A003.b. refers to systems in which ‘inertial measurement equipment or systems’ and other independent ‘positional aiding references’ are built into a single unit (i.e., embedded) in order to achieve improved performance. c. Designed for “aircraft”, land vehicles or vessels, providing heading or True North determination and having any of the following: 1. A maximum operating angular rate less (lower) than 500 deg/s and a heading accuracy without the use of ‘positional aiding references’ equal to or less (better) than 0,07 deg sec(Lat) (equivalent to 6 arc minutes rms at 45 degrees latitude); or 2. A maximum operating angular rate equal to or greater (higher) than 500 deg/s and a heading accuracy without the use of ‘positional aiding references’ equal to or less (better) than 0,2 deg sec(Lat) (equivalent to 17 arc minutes rms at 45 degrees latitude); or d. Providing acceleration measurements or angular rate measurements, in more than one dimension, and having any of the following: 1. Performance specified by 7A001 or 7A002 along any axis, without the use of any aiding references; or 2. Being “space-qualified” and providing angular rate measurements having an “angle random walk” along any axis of less (better) than or equal to 0,1 degree per square root hour. Note: 7A003.d.2. does not control ‘inertial measurement equipment or systems’ that contain “spinning mass gyros” as the only type of gyro.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M9A6Code: 7A003‘Inertial measurement equipment or systems’, having any of the following: N.B.: SEE ALSO 7A103. Note 1: ‘Inertial measurement equipment or systems’ incorporate accelerometers or gyroscopes to measure changes in velocity and orientation in order to determine or maintain heading or position without requiring an external reference once aligned. ‘Inertial measurement equipment or systems’ include: — Attitude and Heading Reference Systems (AHRSs); — Gyrocompasses; — Inertial Measurement Units (IMUs); — Inertial Navigation Systems (INSs); — Inertial Reference Systems (IRSs); — Inertial Reference Units (IRUs). Note 2: 7A003 does not control ‘inertial measurement equipment or systems’ which are certified for use on “civil aircraft” by civil aviation authorities of one or more “participating states”. Technical Notes: 1. ‘Positional aiding references’ independently provide position, and include: a. Global Navigation Satellite Systems (GNSS); b. “Data-Based Referenced Navigation” (“DBRN”). 2. ‘Circular Error Probable’ (‘CEP’) — In a circular normal distribution, the radius of the circle containing 50 % of the individual measurements being made, or the radius of the circle within which there is a 50 % probability of being located. a. Designed for “aircraft”, land vehicles or vessels, providing position without the use of ‘positional aiding references’, and having any of the following accuracies subsequent to normal alignment: 1. 0,8 nautical miles per hour (nm/hr) ‘Circular Error Probable’ (‘CEP’) rate or less (better); 2. 0,5 % distanced travelled ‘CEP’ or less (better); or 3. Total drift of 1 nautical mile ‘CEP’ or less (better) in a 24 hr period; Technical Note: The performance parameters in 7A003.a.1., 7A003.a.2. and 7A003.a.3. typically apply to ‘inertial measurement equipment or systems’ designed for “aircraft”, vehicles and vessels, respectively. These parameters result from the utilisation of specialised non-positional aiding references (e.g., altimeter, odometer, velocity log). As a consequence, the specified performance values cannot be readily converted between these parameters. Equipment designed for multiple platforms are evaluated against each applicable entry 7A003.a.1., 7A003.a.2., or 7A003.a.3. b. Designed for “aircraft”, land vehicles or vessels, with an embedded ‘positional aiding reference’ and providing position after loss of all ‘positional aiding references’ for a period of up to 4 minutes, having an accuracy of less (better) than 10 meters ‘CEP’; Technical Note: 7A003.b. refers to systems in which ‘inertial measurement equipment or systems’ and other independent ‘positional aiding references’ are built into a single unit (i.e., embedded) in order to achieve improved performance. c. Designed for “aircraft”, land vehicles or vessels, providing heading or True North determination and having any of the following: 1. A maximum operating angular rate less (lower) than 500 deg/s and a heading accuracy without the use of ‘positional aiding references’ equal to or less (better) than 0,07 deg sec(Lat) (equivalent to 6 arc minutes rms at 45 degrees latitude); or 2. A maximum operating angular rate equal to or greater (higher) than 500 deg/s and a heading accuracy without the use of ‘positional aiding references’ equal to or less (better) than 0,2 deg sec(Lat) (equivalent to 17 arc minutes rms at 45 degrees latitude); or d. Providing acceleration measurements or angular rate measurements, in more than one dimension, and having any of the following: 1. Performance specified by 7A001 or 7A002 along any axis, without the use of any aiding references; or 2. Being “space-qualified” and providing angular rate measurements having an “angle random walk” along any axis of less (better) than or equal to 0,1 degree per square root hour. Note: 7A003.d.2. does not control ‘inertial measurement equipment or systems’ that contain “spinning mass gyros” as the only type of gyro.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M9A6Code: 7A003‘Inertial measurement equipment or systems’, having any of the following: N.B.: SEE ALSO 7A103. Note 1: ‘Inertial measurement equipment or systems’ incorporate accelerometers or gyroscopes to measure changes in velocity and orientation in order to determine or maintain heading or position without requiring an external reference once aligned. ‘Inertial measurement equipment or systems’ include: — Attitude and Heading Reference Systems (AHRSs); — Gyrocompasses; — Inertial Measurement Units (IMUs); — Inertial Navigation Systems (INSs); — Inertial Reference Systems (IRSs); — Inertial Reference Units (IRUs). Note 2: 7A003 does not control ‘inertial measurement equipment or systems’ which are certified for use on “civil aircraft” by civil aviation authorities of one or more “participating states”. Technical Notes: 1. ‘Positional aiding references’ independently provide position, and include: a. Global Navigation Satellite Systems (GNSS); b. “Data-Based Referenced Navigation” (“DBRN”). 2. ‘Circular Error Probable’ (‘CEP’) — In a circular normal distribution, the radius of the circle containing 50 % of the individual measurements being made, or the radius of the circle within which there is a 50 % probability of being located. a. Designed for “aircraft”, land vehicles or vessels, providing position without the use of ‘positional aiding references’, and having any of the following accuracies subsequent to normal alignment: 1. 0,8 nautical miles per hour (nm/hr) ‘Circular Error Probable’ (‘CEP’) rate or less (better); 2. 0,5 % distanced travelled ‘CEP’ or less (better); or 3. Total drift of 1 nautical mile ‘CEP’ or less (better) in a 24 hr period; Technical Note: The performance parameters in 7A003.a.1., 7A003.a.2. and 7A003.a.3. typically apply to ‘inertial measurement equipment or systems’ designed for “aircraft”, vehicles and vessels, respectively. These parameters result from the utilisation of specialised non-positional aiding references (e.g., altimeter, odometer, velocity log). As a consequence, the specified performance values cannot be readily converted between these parameters. Equipment designed for multiple platforms are evaluated against each applicable entry 7A003.a.1., 7A003.a.2., or 7A003.a.3. b. Designed for “aircraft”, land vehicles or vessels, with an embedded ‘positional aiding reference’ and providing position after loss of all ‘positional aiding references’ for a period of up to 4 minutes, having an accuracy of less (better) than 10 meters ‘CEP’; Technical Note: 7A003.b. refers to systems in which ‘inertial measurement equipment or systems’ and other independent ‘positional aiding references’ are built into a single unit (i.e., embedded) in order to achieve improved performance. c. Designed for “aircraft”, land vehicles or vessels, providing heading or True North determination and having any of the following: 1. A maximum operating angular rate less (lower) than 500 deg/s and a heading accuracy without the use of ‘positional aiding references’ equal to or less (better) than 0,07 deg sec(Lat) (equivalent to 6 arc minutes rms at 45 degrees latitude); or 2. A maximum operating angular rate equal to or greater (higher) than 500 deg/s and a heading accuracy without the use of ‘positional aiding references’ equal to or less (better) than 0,2 deg sec(Lat) (equivalent to 17 arc minutes rms at 45 degrees latitude); or d. Providing acceleration measurements or angular rate measurements, in more than one dimension, and having any of the following: 1. Performance specified by 7A001 or 7A002 along any axis, without the use of any aiding references; or 2. Being “space-qualified” and providing angular rate measurements having an “angle random walk” along any axis of less (better) than or equal to 0,1 degree per square root hour. Note: 7A003.d.2. does not control ‘inertial measurement equipment or systems’ that contain “spinning mass gyros” as the only type of gyro.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M2A1dCode: 7A003‘Inertial measurement equipment or systems’, having any of the following: N.B.: SEE ALSO 7A103. Note 1: ‘Inertial measurement equipment or systems’ incorporate accelerometers or gyroscopes to measure changes in velocity and orientation in order to determine or maintain heading or position without requiring an external reference once aligned. ‘Inertial measurement equipment or systems’ include: — Attitude and Heading Reference Systems (AHRSs); — Gyrocompasses; — Inertial Measurement Units (IMUs); — Inertial Navigation Systems (INSs); — Inertial Reference Systems (IRSs); — Inertial Reference Units (IRUs). Note 2: 7A003 does not control ‘inertial measurement equipment or systems’ which are certified for use on “civil aircraft” by civil aviation authorities of one or more “participating states”. Technical Notes: 1. ‘Positional aiding references’ independently provide position, and include: a. Global Navigation Satellite Systems (GNSS); b. “Data-Based Referenced Navigation” (“DBRN”). 2. ‘Circular Error Probable’ (‘CEP’) — In a circular normal distribution, the radius of the circle containing 50 % of the individual measurements being made, or the radius of the circle within which there is a 50 % probability of being located. a. Designed for “aircraft”, land vehicles or vessels, providing position without the use of ‘positional aiding references’, and having any of the following accuracies subsequent to normal alignment: 1. 0,8 nautical miles per hour (nm/hr) ‘Circular Error Probable’ (‘CEP’) rate or less (better); 2. 0,5 % distanced travelled ‘CEP’ or less (better); or 3. Total drift of 1 nautical mile ‘CEP’ or less (better) in a 24 hr period; Technical Note: The performance parameters in 7A003.a.1., 7A003.a.2. and 7A003.a.3. typically apply to ‘inertial measurement equipment or systems’ designed for “aircraft”, vehicles and vessels, respectively. These parameters result from the utilisation of specialised non-positional aiding references (e.g., altimeter, odometer, velocity log). As a consequence, the specified performance values cannot be readily converted between these parameters. Equipment designed for multiple platforms are evaluated against each applicable entry 7A003.a.1., 7A003.a.2., or 7A003.a.3. b. Designed for “aircraft”, land vehicles or vessels, with an embedded ‘positional aiding reference’ and providing position after loss of all ‘positional aiding references’ for a period of up to 4 minutes, having an accuracy of less (better) than 10 meters ‘CEP’; Technical Note: 7A003.b. refers to systems in which ‘inertial measurement equipment or systems’ and other independent ‘positional aiding references’ are built into a single unit (i.e., embedded) in order to achieve improved performance. c. Designed for “aircraft”, land vehicles or vessels, providing heading or True North determination and having any of the following: 1. A maximum operating angular rate less (lower) than 500 deg/s and a heading accuracy without the use of ‘positional aiding references’ equal to or less (better) than 0,07 deg sec(Lat) (equivalent to 6 arc minutes rms at 45 degrees latitude); or 2. A maximum operating angular rate equal to or greater (higher) than 500 deg/s and a heading accuracy without the use of ‘positional aiding references’ equal to or less (better) than 0,2 deg sec(Lat) (equivalent to 17 arc minutes rms at 45 degrees latitude); or d. Providing acceleration measurements or angular rate measurements, in more than one dimension, and having any of the following: 1. Performance specified by 7A001 or 7A002 along any axis, without the use of any aiding references; or 2. Being “space-qualified” and providing angular rate measurements having an “angle random walk” along any axis of less (better) than or equal to 0,1 degree per square root hour. Note: 7A003.d.2. does not control ‘inertial measurement equipment or systems’ that contain “spinning mass gyros” as the only type of gyro.
Authority: EUProhibited Supply To: IRKPProgram: IREU Code: M2A1dCode: 7A003