Textual Amendments
For radar, see Category 6.
[7A001] Accelerometers as follows and specially designed components therefor:
Linear accelerometers having any of the following:
Specified to function at linear acceleration levels less than or equal to 15 g and having any of the following:
A "bias""stability" of less (better) than 130 micro g with respect to a fixed calibration value over a period of one year; or
A "scale factor""stability" of less (better) than 130 ppm with respect to a fixed calibration value over a period of one year;
Specified to function at linear acceleration levels exceeding 15 g but less than or equal to 100 g and having all of the following:
A "bias""repeatability" of less (better) than 1 250 micro g over a period of one year; and
A "scale factor""repeatability" of less (better) than 1 250 ppm over a period of one year; or
Designed for use in inertial navigation or guidance systems and specified to function at linear acceleration levels exceeding 100 g;
Angular or rotational accelerometers, specified to function at linear acceleration levels exceeding 100 g.
[7A002] Gyros or angular rate sensors, having any of the following and specially designed components therefor:
Specified to function at linear acceleration levels less than or equal to 100 g and having any of the following:
An angular rate range of less than 500 degrees per second and having any of the following:
A "bias""stability" of less (better) than 0,5 degree per hour, when measured in a 1 g environment over a period of one month, and with respect to a fixed calibration value; or
An "angle random walk" of less (better) than or equal to 0,0035 degree per square root hour; or
An angular rate range greater than or equal to 500 degrees per second and having any of the following:
A "bias""stability" of less (better) than 4 degrees per hour, when measured in a 1 g environment over a period of three minutes, and with respect to a fixed calibration value; or
An "angle random walk" of less (better) than or equal to 0,1 degree per square root hour; or
Specified to function at linear acceleration levels exceeding 100 g.
[7A003] ‘Inertial measurement equipment or systems’, having any of the following:
Attitude and Heading Reference Systems (AHRSs);
Gyrocompasses;
Inertial Measurement Units (IMUs);
Inertial Navigation Systems (INSs);
Inertial Reference Systems (IRSs);
Inertial Reference Units (IRUs).
Textual Amendments
F2Words in Annex 1 para. 7A003 Note 2 omitted (31.12.2020) by virtue of The Trade etc. in Dual-Use Items and Firearms etc. (Amendment) (EU Exit) Regulations 2019 (S.I. 2019/771), regs. 1, 3(22)(g) (with reg. 5) (as amended by S.I. 2020/1502, regs. 2(3), 10); 2020 c. 1, Sch. 5 para. 1(1)
‘Positional aiding references’ independently provide position, and include:
"Satellite navigation system";
"Data-Based Referenced Navigation" ("DBRN").
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:
0,8 nautical miles per hour (nm/hr) "Circular Error Probable" ("CEP") rate or less (better);
0,5 % distanced travelled "CEP" or less (better); or
Total drift of 1 nautical mile "CEP" or less (better) in a 24 hr period;
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.
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";
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.
Designed for "aircraft", land vehicles or vessels, providing heading or True North determination and having any of the following:
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
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
Providing acceleration measurements or angular rate measurements, in more than one dimension, and having any of the following:
Performance specified in 7A001 or 7A002 along any axis, without the use of any aiding references; or
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.
[7A004] ‘Star trackers’ and components therefor, as follows:
‘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;
Components specially designed for equipment specified in 7A004.a. as follows:
Optical heads or baffles;
Data processing units.
‘Star trackers’ are also referred to as stellar attitude sensors or gyro-astro compasses.
[7A005] "Satellite navigation system" receiving equipment having any of the following and specially designed components therefor:
Employing a decryption algorithm specially designed or modified for government use to access the ranging code for position and time; or
Employing ‘adaptive antenna systems’.
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.
[7A006] Airborne altimeters operating at frequencies other than 4,2 to 4,4 GHz inclusive and having any of the following:
[7A008] Underwater sonar navigation systems using doppler velocity or correlation velocity logs integrated with a heading source and having a positioning "accuracy" of equal to or less (better) than 3 % of distance travelled "Circular Error Probable" ("CEP") and specially designed components therefor.
See 8A002 for other marine systems.
[7A101] Linear 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 of the following characteristics, and specially designed components therefor:
A "bias""repeatability" of less (better) than 1 250 micro g; and
A "scale factor""repeatability" of less (better) than 1 250 ppm;
[7A102] All types of gyros, other than those specified in 7A002, usable in ‘missiles’, with a rated "drift rate"‘stability’ of less than 0,5o (1 sigma or rms) per hour in a 1 g environment and specially designed components therefor.
[7A103] Instrumentation, navigation equipment and systems, other than those specified in 7A003, as follows; and specially designed components therefor:
‘Inertial measurement equipment or systems’, using accelerometers or gyros as follows:
Accelerometers specified in 7A001.a.3., 7A001.b. or 7A101 or gyros specified in 7A002 or 7A102; or
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’;
‘Inertial measurement equipment or systems’ specified in 7A103.a. incorporate accelerometers or gyros to measure changes in velocity and orientation in order to determine or maintain heading or position without requiring an external reference once aligned.
Attitude and Heading Reference Systems (AHRSs);
Gyrocompasses;
Inertial Measurement Units (IMUs);
Inertial Navigation Systems (INSs);
Inertial Reference Systems (IRSs);
Inertial Reference Units (IRUs).
Integrated flight instrument systems which include gyrostabilisers or automatic pilots, designed or modified for use in ‘missiles’;
‘Integrated navigation systems’, designed or modified for ‘missiles’ and capable of providing a navigational accuracy of 200 m ‘CEP’ or less;
An inertial measurement device (e.g., an attitude and heading reference system, inertial reference unit, or inertial navigation system);
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
Integration hardware and software;
In 7A103.c. ‘CEP’ (Circular Error Probable or Circle of Equal Probability) is a measure of accuracy, defined as the radius of the circle inside of which there is a 50 % probability of being located.
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 of the following characteristics, and specially designed components therefor:
Internal tilt compensation in pitch (± 90 degrees) and roll (± 180 degrees) axes; and
Azimuthal accuracy better (less) than 0,5 degrees rms at latitude of ± 80 degrees, reference to local magnetic field.
In 7A103 ‘missile’ means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.
[7A104] Gyro-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.
[7A105] Receiving equipment for ‘navigation satellite systems’, other than those specified in 7A005, having any of the following characteristics, and specially designed components therefor:
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
Designed or modified for airborne applications and having any of the following:
Capable of providing navigation information at speeds in excess of 600 m/s;
Employing decryption, designed or modified for military or governmental services, to gain access to a ‘navigation satellite system’ secured signal/data; or
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.
In 7A105, ‘navigation satellite system’ includes Global Navigation Satellite Systems (GNSS; e.g., GPS, GLONASS, Galileo or BeiDou) and Regional Navigation Satellite Systems (RNSS; e.g., NavIC, QZSS).
[7A106] Altimeters, 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.
[7A115] Passive 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.
Terrain contour mapping equipment;
Scene mapping and correlation (both digital and analogue) equipment;
Doppler navigation radar equipment;
Passive interferometer equipment;
Imaging sensor equipment (both active and passive).
[7A116] Flight control systems and servo valves, as follows; designed or modified for use in space launch vehicles specified in 9A004, sounding rockets specified in 9A104 or "missiles".
Pneumatic, hydraulic, mechanical, electro-optical, or electro-mechanical flight control systems (including fly-by-wire and fly-by-light systems);
Attitude control equipment;
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.
[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).
In 7A117 ‘CEP’ (Circular Error Probable or 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.]