1. INTRODUCTION
(1) Part 1 of this List
includes missiles and other delivery systems (including
ballistic missiles, cruise missiles, rockets and unmanned
air vehicles) as well as their specially designed items and
technologies. Part 2 includes items and technologies related
to Item 1 of Part 1.
(2) If a Part 1 item is
included in a system, that system will also be considered as
a Part 1 item, except when the incorporated item cannot be
separated, removed or duplicated and the system is designed
for civilian uses, where the item will be considered as a
Part 2 item.
(3) All items listed in this List
include their directly related technologies.
2. DEFINITIONS
For the purpose of
this List, the following definitions apply:
(1)
"Technology" means specific information which is
required for the "development",
"production" or "use" of a product. The
information may take the form of "technical data"
or "technical assistance". But
“technology” does not include technology
"in the public domain" nor "basic scientific
research".
(a) "In the public
domain" as it applies to this List means technology
which has been made available without restrictions upon its
further dissemination. (Copyright restrictions do not remove
technology from being "in the public
domain".)
(b) "Basic scientific
research" means experimental or theoretical work
undertaken principally to acquire new knowledge of the
fundamental principles of phenomena and observable facts,
not primarily directed towards a specific practical aim or
objective.
(2) "Development" is
related to all phases prior to "production" such
as:
(a) Design
(b) Design research
(c) Design analysis
(d) Design
concepts
(e) Assembly and testing of
prototypes
(f) Pilot production schemes
(g) Design data
(h) Process of
transforming design data into a product
(i)
Configuration design
(j) Integration system
design
(k) Layouts
(3)
"Production" means all production phases such
as:
(a) Production engineering
(b)
Manufacture
(c) Integration
(d)
Assembly
(e) Inspection
(f)
Testing
(g) Quality assurance
(4) "Use" means:
(a)
Operation
(b) Installation (including on-site
installation)
(c) Maintenance
(d) Repair
(e) Overhaul
(f) Refurbishing
(5)
"Technical data" may take forms such
as:
(a) Blueprints
(b)
Plans
(c) Diagrams
(d)
Models
(e) Formulae
(f)
Engineering designs and specifications
(g)
Manuals and instructions written or recorded on other media
or devices such as disk, tape, read-only
memories.
(6) "Technical assistance"
may take forms such as:
(a) Instruction
(b) Skills
(c) Training
(d) Working knowledge
(e)
Consulting services
(7) "Production
facilities" means equipment and specially designed
software therefor integrated into installations for
"development" or for one or more phases of
"production".
(8) "Production
equipment" means tooling, templates, jigs, mandrels,
moulds, dies, fixtures, alignment mechanisms, test
equipment, other machinery and components therefor, limited
to those specially designed or modified for
"development" or for one or more phases of
"production".
PART I
1.
Complete ballistic missiles, space launch vehicles, sounding
rockets, cruise missile and unmanned air vehicles that can
be used to deliver at least a 500 kg payload to a range of
at least 300 km as well as the specially designed production
facilities therefor.
2. The following items
usable in the systems in Item 1:
(1) Individual
stages of a ballistic missile;
(2) Individual
stages of a rocket;
(3) Reentry vehicles of
missiles;
(4) Heat shields and components
fabricated of ceramic materials used in Subitem
(3);
(5) Heat shields and components fabricated
of ablative materials used in Subitem (3);
(6)
Heat sinks and components fabricated of light-weight, high
heat capacity materials used in Subitem
(3);
(7) Electronic equipment specially
designed for Subitem (3);
(8) Storable liquid
propellant rocket engines, having a thrust force of 90 kN or
greater;
(9) Solid propellant rocket engines,
having a total impulse capacity of 1100 kN·s or
greater;
(10) Guidance sets capable of
achieving system accuracy of 10 km or less (CEP) for
ballistic missiles with a range of 300 km;
(11)
Thrust vector control sub-systems;
(12) Warhead
safing, arming, fuzing, and firing
mechanisms;
(13) Production facilities and
equipments designed for Subitems (1) to
(12).
3. Interstage mechanisms for space launch
vehicles and the specially designed production equipment
therefor.
4. Rocket motor cases and the
specially designed production equipment
therefor.
5. Hydraulic, mechanical,
electro-optical, or electro-mechanical flight control
systems specially designed or modified for the systems in
Item 1 of Part I.
6. Attitude control equipment
specially designed or modified for the systems in Item 1 of
Part I.
7. Design technology for integration of
air vehicle fuselage, propulsion system and lifting control
surfaces to optimize aerodynamic performance throughout the
flight regime of an unmanned air vehicle.
8.
Design technology for integration of the guidance, flight
control, and propulsion data into a flight management system
for optimization of trajectory of ballistic missiles or
space launch vehicles.
9. Passive
interferometer equipment usable in the systems in Item
1.
10. Apparatus and devices designed or
modified for the handling, control, activation and launching
of the systems in Item 1.
11. Vehicles designed
or modified for the transport, handling, control, activation
and launching of the systems in Item 1.
12.
Gravity meters, gravity gradiometers, and specially designed
components therefor, for airborne or marine use, and having
a static or operational accuracy of one milligal or better,
with a time to steady-state registration of two minutes or
less;
13. Precision
tracking systems:
(1) Tracking systems which
use a translator installed on the rocket system or unmanned
air vehicle in conjunction with either surface or airborne
references or navigation satellite systems to provide
real-time measurements of in-flight position and
velocity;
(2) Software which processes
post-flight, recorded data, enabling determination of
vehicle position throughout its flight
path.
14. Structure specially designed for
reduced radar reflectivity.
15. Structural
material specially designed for reduced radar
reflectivity.
16. Coatings specially designed
for reduced radar reflectivity.
17. Coatings
specially designed for reduced optical reflectivity or
emissivity.
18. Production equipment,
technology and specially designed software usable in Items
14 to 17 above.
19. Technology and specially
designed software for reduced radar reflectivity,
ultraviolet/infrared signatures or acoustic
signatures.
PART II
1. Reentry
Vehicle Components and Technology Thereof
(1)
Design and manufacturing technology for ceramic heat
shields;
(2) Design and manufacturing
technology for ablative heat shields;
(3)
Design and manufacturing technology for heat sinks and
components thereof;
(4) Structure for
protection against electromagnetic pulse (EMP) and X-rays
and shock wave and combined blast and thermal effects:
(a) Radiation-hardened microcircuits and
detectors;
(b) Hardened radome structure
designed to withstand a combined thermal shock greater than
418 J/cm2 accompanied by a peak over pressure of greater
than 50 kPa.
(5) Design technology for
radiation hardenning;
(6) Design technology for
hardened structure.
2. Propulsion Components
and Technology Thereof
(1) Lightweight turbojet
engines that are small and fuel efficient;
(2)
Lightweight turbofan engines that are small and fuel
efficient;
(3) Lightweight turbocompound
engines that are small and fuel efficient;
(4)
Ramjet engines;
(5) Scramjet
engines;
(6) Pulse jet
engines;
(7) Combined cycle
engines;
(8) Devices to regulate combustion for
the above Subitems (4) to (7);
(9) Liquid and
slurry propellant control systems, and specially designed
components thereof, designed or modified to operate in
vibration environments of more than 10 g (RMS) between 20 Hz
and 2,000 Hz:
(a) Servo valves designed for
flow rates of 24 liters per minute or greater, at an
absolute pressure of 7,000 kPa or greater, that have an
actuator response time of less than 100 microseconds;
(b) Pumps, for liquid propellants, with shaft
speeds equal to or greater than 8,000 RPM or with discharge
pressures equal to or greater than 7,000
kPa.
(10) Production facilities specially
designed for the above Subitems (1) to (9).
3.
Liquid Propellants
(1) Hydrazine with a
concentration of more than 70 percent;
(2)
Unsymmetric dimethylhydrazine (UDMH);
(3)
Monomethylhydrazine (MMH);
(4) Mixed
amine;
(5) Dinitrogen
tetroxide;
(6) Red Fuming Nitric
Acid.
4. Solid Propellant and Propellant
Constituents
(1) Metal fuels with particle
sizes less than 500 μm, whether spherical, atomized,
spheroidal, flaked or ground, consisting of 97 percent by
weight or greater of any of the following metal and alloys
of these:
(a) Zirconium;
(b)
Boron;
(c) Magnesium;
(d)
Titanium;
(e) Uranium;
(f)
Tungsten;
(g) Zinc;
(h)
Cerium.
(2) Ammonium perchlorate with particle
sizes less than 500 μm;
(3) Spherical
aluminum powder meeting the following
requirements:
(a) With particle of uniform
diameter;
(b) With aluminum content of 97
percent or greater;
(c) With diameter of less
than 500 μm.
(4) Boron Slurry, having an
energy density of more than 40 x 106 J/kg;
(5)
Nitro-amines:
(a)
Cyclotetramethylene-tetranitramene (HMX);
(b)
Cyclotrimethylene-trinitramine (RDX).
(6)
Composite Propellants:
(a) Molded colloid
propellants;
(b) Propellant including nitrate
bonding agents and with an aluminum (particle) content of 5
percent or greater.
(7) Polymeric
substances:
(a) Carboxl-terminated
polybutadiene (CTPB);
(b) Hydroxy-terminated
polybutadiene (HTPB).
(8) Triethylamine as an
igniting agent.
5. Guidance and Control Set,
Components and Related Technologies
(1)
Gyro-astro compasses and other devices which derive position
or orientation by means of automatically tracking celestrial
bodies or satellites;
(2) Flight control
software and related test software;
(3) Gyro
stability platform;
(4) Automatic pilots for
UAV;
(5) Gyros with a rated drift rate
stability of less than 0.5 degree per hour;
(6)
Test table for inertial platform (including high-accuracy
centrifuges and rotating table);
(7) Inertial
Measurement Unit (IMU) tester;
(8) Inertial
Measurement Unit (IMU) stable element handling
fixture;
(9) Inertial Measurement Unit (IMU)
platform balance fixture;
(10) Tester for gyro
tuning;
(11) Tester for gyro dynamic
balance;
(12) Gyro run-in/motor test
station;
(13) Gyro evacuation and filling
station;
(14) Centrifuge fixture for gyro
bearings;
(15) Rectangular scatterometer for
ring laser gyro production;
(16) Polarity
scatterometer for ring laser gyro
production;
(17) Reflectometer for ring laser
gyro production;
(18) Surface profilometer for
ring laser gyro production;
(19) Accelerometers
with a proportional error of 0.25 percent or
less;
(20) Accelerometer test
station;
(21) Accelerometer axis align
station;
(22) Specially designed test,
calibration, and alignment equipment for gyro or
accelerometer.
6. Target Detection System and
Related Electronics
(1) Radar
systems;
(2) Altimeters;
(3)
Terrain contour mapping equipment;
(4) Scene
mapping and correlation (both digital and analog)
equipment;
(5) Imaging sensor
equipment;
(6) Processors and software
specially designed for processing navigation
information;
(7) Electronic devices and
components removed of conductive heat;
(8)
Radiation-hardened electronic devices and
components;
(9) Electronic assemblies and
components operating at temperatures in excess of 125
°C for a short period of
time;
(10)Electronic devices and components
with specially designed integrated
support;
(11) Telemetry equipment and related
technologies;
(12) Telemetering and telecontrol
ground equipment;
(13) Analogue computers and
digital computers having either of the following
characteristics:
(a) Rated for continuous
operation at temperatures from below minus 45 °C to
above plus 55 °C;
(b) Designed as
ruggedized or radiation hardened.
(14)
Analogue-to-digital converter having one of the following
characteristics:
(a) Rated for operation at
temperatures from below minus 54 °C to above plus 125
°C, and
(b) Designed to meet military
specifications for ruggedized equipment; or
(c) Designed or modified for military use or
designed as radiation hardened, and having one of the
following characteristics:
① Converting
at a rate of over 200000 times (complete conversion) per
second under rated accuracy;
② With
accuracy exceeding 1/10000 of the whole range in the rated
temperature scope;
③With quality factor
of over 1´108 (complete conversion times per second
divided by accuracy);
④The inbuilt
microcircuits having the following
characteristics:
(A) The maximum converting
time is less than 20 microseconds under maximum resolution,
and
(B) The rated nonlinearity is better than
0.025 percent of the range in rated temperature
scope.
(15) Design technology for protection of
avionics and electrical subsystems against electromagnetic
pulse and electromagnetic interference hazards from external
sources:
(a) Design technology for shielding
systems;
(b) Design technology for the
configuration of hardened electrical circuits and
subsystems;
(c) Determination of hardening
criteria for the above.
7.
Material
(1) Structural composites, including
composite structures, laminates, and manufactures thereof,
and resin impregnated fibre prepregs and metal coated fibre
preforms therefor, made with either organic matrix or metal
matrix utilizing fibrous or filamentary reinforcements
having a specific tensile strength greater than 7.62 x 104 m
and a specific modulus greater than 3.18 x 106
m:
(a) Polyimide composite;
(b)
Polyamide composite;
(c) Polycarbonate
composite;
(d) Quartz-fibre-reinforced
composite;
(e) Carbon-fibre-reinforced
composite;
(f) Boron-fibre-reinforced
composite;
(g) Magnesium matrix
composite;
(h) Titanium matrix
composite.
(2) Ceramic composite materials with
dielectric constant less than 6 at frequencies from 100 Hz
to 10,000 MHz;
(3) Fine grain bulk artificial
graphites having the following features measured at 20
°C:
(a) With a bulk density of at least
1.72 g/cm3;
(b) With a tension rupture strain
of at least 0.7 percent;
(c) With a heat
expansion coefficient of at least 2.75´10-6 (measured
at temperatures from 20 °C to 982
°C).
(4) Resaturated pyrolized
carbon-carbon materials;
(5) Special
Steel:
Titanium-stabilized duplex stainless
steel (Ti-DSS) having the following
characteristics:
(a) Containing 17.0 to 26.5
weight percent chromium and 4.5 to 7.0 weight percent
nickel;
(b) Having a ferritic-austenitic
microstructure (also referred to as a two-phase
microstructure) of which at least 10 percent is austenite by
volume;
(c) Having any of the following
forms:
① Ingots or bars having a size of
100 mm or more in each dimension;
②
Sheets having a width of 600 mm or more and a thickness of 3
mm or less;
③ Tubes having an outer
diameter of 600 mm or more and a wall thickness of 3 mm or
less.
(6) Ceramic heat shielding
material;
(7) Ablative heat shielding
material.
8. Design and Test Equipment and
Technologies Related to Ballistic Missiles and
Rockets
(1) Specially designed software, or
analogue and digital computers thereof, for modeling,
simulation, or design integration of the
systems;
(2) Vibration test systems capable of
providing a force of 100kN or more and incorporating a
digital controller, as well as specially designed vibration
test auxiliaries and software;
(3) Wind-tunnel
for supersonic (Mach 1.4 to 5) or hypersonic (Mach 5 to 15)
speeds except those specially designed for teaching and
those with the test area dimensions smaller than 25 cm
(measured internally);
(4) Test benches which
have the capacity to handle solid or liquid propellant
rocket motors of more than 90 kN of thrust, or which are
capable of simultaneously measuring the three axial thrust
components.
9. Production Equipment and
Production Technology
(1) Equipment for
production of solid propellants listed in Item 4 of Part
II:
(a) Batch mixers
having:
① A total volumetric capacity of
110 litres or more; and
② At least one
mixing/kneading shaft mounted off centre.
(b)
Continuous mixers having:
① Two or more
mixing/kneading shafts; and
② Capability
to open the mixing chamber.
(c) Equipment for
the production of atomized or spherical metallic powder in a
controlled environment;
(d) Fluid energy
mills;
(e) Handling equipment for production of
solid propellant;
(f) Curing equipment for
production of solid propellant;
(g) Casting
equipment for production of solid
propellant;
(h) Pressing equipment for
production of solid propellant;
(i) Acceptance
testing equipment for production of solid
propellant;
(j) Machining equipment for
production of solid propellant;
(k) Extruding
equipment for production of solid
propellant.
(2) Equipment for producing liquid
propellant in Item 3 of Part II:
(a) Handling
equipment for production of liquid
propellant;
(b) Production equipment for liquid
propellant;
(c) Acceptance testing equipment
for production of liquid propellant.
(3)
Pyrolytic deposition and densification equipment and
technology
(a) Technology for producing
pyrolytically derived materials formed on a mould, mandrel
or other substrate from precursor gases which decompose at
temperatures from 1,300 °C to 2,900 °C and at
pressures of 130 Pa to 20 kPa, including technology for the
composition of precursor gases, flow-rates and process
control schedules and parameters;
(b) Specially
designed nozzles for the above processes;
(c)
Isostatic presses having all of the following
characteristics:
① Maximum working
pressure of 69 MPa or greater;
②Designed
to achieve and maintain a controlled thermal environment of
600 °C or greater, and
③ Possessing
a chamber cavity with an inside diameter of 254 mm or
greater.
(d) Chemical vapor deposition furnaces
for the densification of carbon-carbon
composites;
(e) Pyrolytic deposition and
densification process controls equipment and specially
designed software therefor.
(4) Equipment and
technology for production of composite
component:
(a) Filament winding machines
coordinated and programmed in three or more axes, and
specially designed computers and software
thereof;
(b) Tape-laying machines coordinated
and programmed in two or more axes, and specially designed
software thereof;
(c) Adapters and modification
kits of weaving machines for fibre structure
composites;
(d) Technical data and procedures
for the regulation of temperature, pressures or atmosphere
in autoclaves or hydroclaves;
(e) Equipment for
converting polymeric fibres (such as polyacrylonitrile,
rayon or polycarbosilane) including special provision to
strain the fibre during heating;
(f) Equipment
for the vapor deposition of elements or compounds on heated
filament substrates;
(g) Equipment for the
wet-spinning of refractory ceramics (such as aluminium
oxide);
(h) Equipment for special fibre surface
treatment;
(i) Equipment for producing prepregs
and preforms;
(j) Moulds, mandrels, dies,
fixtures and tooling for the preform pressing, curing,
casting, sintering or bonding of composite structures,
laminates and manufactures thereof.