N.B.: For automatic pilots for underwater vehicles, see Category 8. For radar, see Category 6.
7A001 Accelerometers as follows and specially designed components therefor:
N.B.: SEE ALSO 7A101.
N.B.: For angular or rotational accelerometers, see 7A001.b.
a. Linear accelerometers having any of the following:
1. Specified to function at linear acceleration levels less than or equal to 15 g and having any of the following:
a. A “bias” “stability” of less (better) than 130 micro g with respect to a fixed calibration value over a period of one year; or
b. A “scale factor” “stability” of less (better) than 130 ppm with respect to a fixed calibration value over a period of one year;
2. Specified to function at linear acceleration levels exceeding 15 g and having all of the following:
a. A “bias” “repeatability” of less (better) than 1,250 micro g over a period of one year; and
b. A “scale factor” “repeatability” of less (better) than 1,250 ppm over a period of one year; or
3. Designed for use in inertial navigation or guidance systems and specified to function at linear acceleration levels exceeding 100 g;
Note: 7A001.a.1. and 7A001.a.2. do not apply to accelerometers limited to measurement of only vibration or shock.
b. 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:
N.B.: SEE ALSO 7A102.
N.B.: For angular or rotational accelerometers, see 7A001.b.
a. Specified to function at linear acceleration levels less than or equal to 100 g and having any of the following:
1. A rate range of less than 500 degrees per second and having any of the following:
a. 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
b. An “angle random walk” of less (better) than or equal to 0.0035 degree per square root hour; or
Note: 7A002.a.1.b. does not apply to “spinning mass gyros”.
2. A rate range greater than or equal to 500 degrees per second and having any of the following:
a. 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
b. An “angle random walk” of less (better) than or equal to 0.1 degree per square root hour; or
Note: 7A002.a.2.b. does not apply to “spinning mass gyros”.
b. Specified to function at linear acceleration levels exceeding 100 g.
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:
a. Attitude and Heading Reference Systems (AHRSs);
b. Gyrocompasses;
c. Inertial Measurement Units (IMUs);
d. Inertial Navigation Systems (INSs);
e. Inertial Reference Systems (IRSs);
f. Inertial Reference Units (IRUs).
Note 2: 7A003. does not apply to ‘inertial measurement equipment or systems’ which are certified for use on “civil aircraft” by civil aviation authorities and one or more Wassenaar Arrangement Participating States.
‘Positional aiding references’ independently provide position, and include:
a. Global Navigation Satellite Systems (GNSS);
b. “Data‑Based Referenced Navigation” (“DBRN”).
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% distance travelled “CEP” or less (better); or
3. 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.
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”;
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);
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 apply to ‘inertial measurement equipment or systems’ that contain “spinning mass gyros” as the only type of gyro.
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 by 7A004.a. as follows:
1. Optical heads or baffles;
2. Data processing units.
‘Star trackers’ are also referred to as stellar attitude sensors or gyro‑astro compasses.
7A005 Global 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 apply to 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.
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:
N.B.: SEE ALSO 7A106.
a. ‘Power management’; or
b. Using phase shift key modulation.
‘Power management’ is changing the transmitted power of the altimeter signal so that received power at the “aircraft” altitude is always at the minimum necessary to determine the altitude.
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.
Note: 7A008 does not apply to systems specially designed for installation on surface vessels or systems requiring acoustic beacons or buoys to provide positioning data.
N.B.: See 6A001.a. for acoustic systems, and 6A001.b. for correlation‑velocity and Doppler‑velocity sonar log equipment. See 8A002 for other marine systems.
7A101 Linear accelerometers, other than those specified by 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 1250 micro g; and
b. A “scale factor” “repeatability” of less (better) than 1250 ppm;
Note: 7A101 does not specify accelerometers which are specially designed and developed as MWD (Measurement While Drilling) Sensors for use in downhole well service operations.
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;
7A102 All types of gyros, other than those specified by 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.
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).
3. In 7A102 ‘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 2.56).
7A103 Instrumentation, navigation equipment and systems, other than those specified by 7A003, as follows; and specially designed components therefor:
a. ‘Inertial measurement equipment or systems’, using accelerometers or gyros as follows:
1. Accelerometers specified by 7A001.a.3., 7A001.b. or 7A101 or gyros specified by 7A002 or 7A102;
2. Accelerometers specified by 7A001.a.1. or 7A001.a.2. and having all of the following:
a. Designed for use in inertial navigation systems or in guidance systems of all types and usable in ‘missiles’;
b. A “bias” “repeatability” of less (better) than 1250 micro g; and
c. A “scale factor” “repeatability” of less (better) than 1250 ppm;
Note 1: 7A103.a includes:
a. Attitude and Heading Reference Systems (AHRSs);
b. Gyrocompasses;
c. Inertial Measurement Units (IMUs);
d. Inertial Navigation Systems (INSs);
e. Inertial Reference Systems (IRSs);
f. Inertial Reference Units (IRUs).
Note 2: 7A103.a does not specify equipment containing accelerometers specified by 7A001 where such accelerometers are specially designed and developed as MWD (Measurement While Drilling) sensors for use in down‑hole well services operations.
‘Inertial measurement equipment or systems’ specified by 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.
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 “Circular Error Probable” (“CEP”) or less;
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;
d. Three axis magnetic heading sensors, designed or modified to be integrated with flight control and navigation systems, 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 gyrostabilisers, automatic pilots and inertial navigation systems.
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 by 7A004, which derive position or orientation by means of automatically tracking celestial bodies or satellites and specially designed components therefor.
7A105 Receiving equipment for Global Navigation Satellite Systems (GNSS; e.g. GPS, GLONASS, Galileo or BeiDou), having any of the following characteristics, and specially designed components therefor:
a. Designed or modified for use in space launch vehicles specified by 9A004, unmanned aerial vehicles specified by 9A012 or 9A112.a or sounding rockets specified by 9A104; 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 apply to equipment designed for commercial, civil or ‘Safety of Life’ (e.g., data integrity, flight safety) GNSS services.
7A106 Altimeters, other than those specified by 7A006, of radar or laser radar type, designed or modified for use in space launch vehicles specified by 9A004 or sounding rockets specified by 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 by 9A004 or sounding rockets specified by 9A104.
Note: 7A115 includes sensors for the following equipment:
a. Terrain contour mapping equipment;
b. Scene mapping and correlation (both digital and analogue) equipment;
c. Doppler navigation radar equipment;
d. Passive interferometer equipment;
e. 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 by 9A004 or sounding rockets specified by 9A104.
a. Pneumatic, hydraulic, mechanical, electro‑optical, or electromechanical flight control systems (including fly‑by‑wire and fly‑by‑light systems);
b. Attitude control equipment;
c. Flight control servo valves designed or modified for the systems specified by 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).