Components specially designed for solid rocket propulsion systems, as follows: N.B.: SEE ALSO 9A108. a. Insulation and propellant bonding systems, using liners to provide a ‘strong mechanical bond’ or a barrier to chemical migration between the solid propellant and case insulation material; Technical Note: ‘Strong mechanical bond’ means bond strength equal to or more than propellant strength.

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Notes

• Rocket motor cases, ‘insulation’ components and nozzles therefor, usable in the systems specified in 1.A. or 19.A.1. 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.
• ‘Insulation’ material in bulk form usable for rocket motor cases in the subsystems specified in 2.A.1.c.1. or specially designed for subsystems specified in 20.A.1.b.1.Technical Note:In 3.C.2. ‘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 sheet stock containing an insulating or refractory material. It may also be incorporated as stress relief boots or flaps specified in 3.A.3.
• 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.
• ‘Interior lining’ usable for rocket motor cases in the subsystems specified in 2.A.1.c.1. or specially designed for subsystems specified in 20.A.1.b.1.Technical Note:In 3.C.1. ‘interior lining’ suited for the bond interface between the solid propellant and the case or insulating liner is usually a liquid polymer based dispersion of refractory or insulating materials e.g. carbon filled HTPB or other polymer with added curing agents to be sprayed or screeded over a case interior.