c. Thrust vector control sub-systems, usable in “missiles”. Technical Note: Examples of methods of achieving thrust vector control specified in 9A108.c. are: 1. Flexible nozzle; 2. Fluid or secondary gas injection; 3. Movable engine or nozzle; 4. Deflection of exhaust gas stream (jet vanes or probes); or 5. Thrust tabs.

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Prohibited Supply To

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Document

Notes

• Rocket motor cases, ‘insulation’ components and nozzles therefor, usable in the systems specified in 1.A. or 19.A.1.
• 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 that do not exceed the “range”/“payload” capability of systems specified in 1.A.;Technical Note:2.A.1.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.
• Technical Note:In 3.A.3. ‘insulation’ intended to be applied to the components of a rocket motor, i.e. the case, nozzle inlets, case closures, includes cured or semi-cured compounded rubber components comprising sheet stock containing an insulating or refractory material. It may also be incorporated as stress relief boots or flaps.Note:Refer to 3.C.2. for ‘insulation’ material in bulk or sheet form.