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Composite propellants are heterogeneous mixtures of fuels and small particulate oxidizers held together by a rubbery material referred to as the binder. They provide a stable, high-performance, solid propellant for rocket motors.
Composite propellants are used to provide the propulsive energy for rocket systems, kick motors for satellites, and for booster motors for launching cruise missiles and Unmanned Air Vehicles (UAVs).
Ammonium Perchlorate
Ammonium Perchlorate is the oxidizing component of choice when dealing with solid rocket motor propellants. IPI supplies NH4NO3 in accordance with the following specifications:
- MIL-A-192B
- MIL-A-82667/2 (OS)
- MIL-A-82667/1 (OS)
- MIL-A-23946 (WEP)
- MIL-A-23948 (AS)
Ammonium Perchlorate is available in the following particle sizes:
- 400 microns
- 200 microns
- 90 microns
- 50 microns
- 20 microns
- 2.5 microns
Aluminum Powder
Aluminum powder is the most commonly used fuel component of composite propellants. It provides better performance and greater ease of use than other metal powders that may be used. Aluminum powder is used to increase the specific impulse of the propellant and to help stabilize combustion.
IPI supplies aluminum powder in accordance with the MIL-A-82728 (OS) specification.
Carboxyl Terminated Polybutadiene Linear (CTPB)
CTPB, a form of synthetic rubber, is used as a binder for composite propellants. Carboxyl Terminated Polybutadiene Linear is one of the best synthetic rubbers for this application.
IPI supplies CTPB in accordance with the MIL-PRF-23942A (AS) specification.
Hydroxyl Terminated Polybutadiene (HTPB)
HTPB, a form of synthetic rubber, is used as a binder for composite propellants. Hydroxyl Terminated Polybutadiene (HTPB), much like Carboxyl Terminated Polybutadiene Linear (CTPB), is one of the best synthetic rubbers for this application.
IPI supplies HTPB in accordance with the MIL-H-85497 specification.
Catocene (2,2-Bis-ethylferrocenyl propane)
Catocene is an excellent iron-based burn rate catalyst used in composite propellant formulations. It can be used to formulate propellants to yield a burn rate of one inch per second or more.
Dioctyl Adipate
MIL-D-85494 specification. Plasticizer.
Di-(2-Ethylhexyl) Adipate
DOD-D-23443B specification. Plasticizer.
Dioctyl Sebacate (DOS)
CAS: 122-62-3.
Di-(2-ethyl-hexyl) Sebacate
MIL-D-10692 specification.
Triphenyl Bismuth
MIL-T-82825; MIL-T-70681; WS-20883 specifications. Cure catalyst, bonding and accelerating agent.
Dimeryl Diisocyanate (DDI)
MIL-C-85498(AS) Type I; MIL-D-82675(OS) specification. Curing agent in solid propellants.
Isophorone Diisocyanate (IPDI)
MIL-C-85498(AS) Type II; WS-16305C specifications. Curing agent in solid propellants.
MAPO (Tris-1-(2-Methyl) aziridinyl) phosphine oxide)
DOD-T-82666A specification. MAPO is a curing agent for CTPB pre-polymers and a bonding agent for HTPB pre-polymers.
HX-868
Trimesol-1 (2ethyl) Aziridine Liner Adhesion
HX-878 “Tepanol”
MIL-T-82824 Reaction product of tet enepentamine and acrylonitrile.
HX-879 “Tepan”
Reaction product of tet enepentamine and acrylonitrile.
HX-752, HX-872, and HX-877
Polyfunctional aziridine amides with isophtalic, trimesic, isocyanuric, or trimethyladipic backbone also having a 2-methyl or 2-ethyl aziridine group.
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