7A103Instrumentation, navigation equipment and systems, other than those specified in 7A003, as follows; and specially designed components therefor:

a. 'Inertial measurement equipment or systems', using accelerometers or gyros as follows:
1. Accelerometers specified in 7A001.a.3., 7A001.b. or 7A101 or gyros specified in 7A002 or 7A102; or
Note:
7A103.a.1. does not control equipment containing accelerometers specified in 7A001.a.3. that are designed to measure vibration or shock.
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.2. does not control equipment containing accelerometers specified in 7A001.a.1. or 7A001.a.2. where such accelerometers are specially designed and developed as MWD (Measurement While Drilling) sensors for use in down-hole well services operations
Technical Note:
'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.
Note
:
'Inertial measurement equipment or systems' in 7A103.a. include:
—
Attitude and Heading Reference Systems (AHRSs);
—
Gyrocompasses;
—
Inertial Measurement Units (IMUs);
—
Inertial Navigation Systems (INSs);
—
Inertial Reference Systems (IRSs);
—
Inertial Reference Units (IRUs).
b. Integrated flight instrument systems which include gyrostabilisers or automatic pilots, designed or modified for use in 'missiles';
c. 'Integrated navigation systems', designed or modified for 'missiles' and capable of providing a navigational accuracy of 200 m 'CEP' or less;
Technical Notes:
1. An 'integrated navigation system' typically incorporates the following components:
a. An inertial measurement device (e.g., an attitude and heading reference system, inertial reference unit, or inertial navigation system);
b. 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
c. Integration hardware and software;
2. 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.
d. 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:
1. Internal tilt compensation in pitch (± 90 degrees) and roll (± 180 degrees) axes; and
2. 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 gyrostabilisers, 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.