- List
- MTCR – Equipment, Software and Technology Annex – Version of 14 March 2024
a. Individual rocket stages usable in the systems specified in 1.A.;
b. Re-entry vehicles usable in the systems specified in 1.A., and, as follows, equipment designed or modified therefor, except as provided in the Note below 2.A.1. for those designed for non-weapon payloads:
1. Heat shields and components therefor, fabricated of ceramic or ablative materials;
2. Heat sinks and components therefor, fabricated of light-weight, high heat capacity materials;
3. Electronic equipment specially designed for re-entry vehicles;
c. Rocket propulsion subsystems, usable in the systems specified in 1.A., as follows;
1. Solid propellant rocket motors or hybrid rocket motors having a total impulse capacity equal to or greater than 1.1 x 10⁶ Ns;
2. Liquid propellant rocket engines or gel propellant rocket motors integrated, or designed or modified to be integrated, into a liquid propellant or gel propellant propulsion system which has a total impulse capacity equal to or greater than 1.1 x 10⁶ Ns;
Note:
Liquid propellant apogee engines or station-keeping engines specified in 2.A.1.c.2., 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.
d. '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. for those designed for missiles with a "range" under 300 km or manned aircraft;
Technical Notes:
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.
2. In Item 2.A.1.d., '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.
e. Thrust vector control subsystems, usable in the systems specified in 1.A., except as provided in the Note below 2.A.1. for those designed for rocket systems other than those specified in 1.A.;
Technical Note:
e. includes the following methods of achieving thrust vector control:
a. Flexible nozzle;
b. Fluid or secondary gas injection;
c. Movable engine or nozzle;
d. Deflection of exhaust gas stream (jet vanes or probes);
e. Use of thrust tabs.
f. 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.
Note:
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.
b. Re-entry vehicles usable in the systems specified in 1.A., and, as follows, equipment designed or modified therefor, except as provided in the Note below 2.A.1. for those designed for non-weapon payloads:
1. Heat shields and components therefor, fabricated of ceramic or ablative materials;
2. Heat sinks and components therefor, fabricated of light-weight, high heat capacity materials;
3. Electronic equipment specially designed for re-entry vehicles;
c. Rocket propulsion subsystems, usable in the systems specified in 1.A., as follows;
1. Solid propellant rocket motors or hybrid rocket motors having a total impulse capacity equal to or greater than 1.1 x 10⁶ Ns;
2. Liquid propellant rocket engines or gel propellant rocket motors integrated, or designed or modified to be integrated, into a liquid propellant or gel propellant propulsion system which has a total impulse capacity equal to or greater than 1.1 x 10⁶ Ns;
Note:
Liquid propellant apogee engines or station-keeping engines specified in 2.A.1.c.2., 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.
d. '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. for those designed for missiles with a "range" under 300 km or manned aircraft;
Technical Notes:
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.
2. In Item 2.A.1.d., '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.
e. Thrust vector control subsystems, usable in the systems specified in 1.A., except as provided in the Note below 2.A.1. for those designed for rocket systems other than those specified in 1.A.;
Technical Note:
e. includes the following methods of achieving thrust vector control:
a. Flexible nozzle;
b. Fluid or secondary gas injection;
c. Movable engine or nozzle;
d. Deflection of exhaust gas stream (jet vanes or probes);
e. Use of thrust tabs.
f. 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.
Note:
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.