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Hydroxyl Finished Polybutadiene (Htpb) as a Component in Composite Powder and Bonding Layers for Rocket Engines Hydroxyl terminated Polybutadiene (Htpb) Somkomponent I Kompositkrut och Bindeskikt Foer Raketmotorer.

N7917020

Publication Date	1978
Personal Author	Nilsson, B.; Sanden, R.
Page Count	31
Abstract	Small amounts of various composite powders containing 85 and 86% perchlorate of ammonium and with HTPB types R-45HT, R-45M, and CS-15 as fuel bonding substance were manufactured. Three different alifact diisocyanates (DDI 1410, IPDI, and TMDI) were used as hardeners. No particular difference between the three hardeners in respect to drag resistance of the powders was noted. In a corresponding comparison between the three HTPB-types, no significant difference was noted between R-45HT and R-45M, whereas better values were obtained at room temperature with CS-15 as bonding substance. At 50 C the stretching of the CS-15 powders amounts to only a few percent due to the high gas conversion temperature of this polymer. Working time for the powder masses is approximately 4 hrs at 53 C with R-45HT or R-45M as bonding substance and DDI as hardener. Experiments were carried out to manufacture materials that could be used as a bonding layer between HTPB powder and rocket engines shell. Materials with good resistance and adherence to both powder and blasted, primer treated steel plate were developed. Of these materials, the bonding part is based on R-45HT and carbon black is the main filler. They are DDI hardened.
Keywords	Composite propellants Hydroxyl compounds Polybutadiene Propellant binders Propellant chemistry Solid propellant rocket engines Ammonium perchlorates Carbon Diisocyanates Hardening(Materials) Solid rocket propellants Hydroxyl terminated polybutadiene Sweden
Source Agency	NASA Foreign Exchange Program
NTIS Subject Category	81H - Rocket Propellants
Corporate Authors	Research Inst. of National Defence, Stockholm (Sweden).
Supplemental Notes	Test in Swedish.
Document Type	Technical Report
NTIS Issue Number	197912

Hydroxyl Finished Polybutadiene (Htpb) as a Component in Composite Powder and Bonding Layers for Rocket Engines Hydroxyl terminated Polybutadiene (Htpb) Somkomponent I Kompositkrut och Bindeskikt Foer Raketmotorer.

Hydroxyl Finished Polybutadiene (Htpb) as a Component in Composite Powder and Bonding Layers for Rocket Engines Hydroxyl terminated Polybutadiene (Htpb) Somkomponent I Kompositkrut och Bindeskikt Foer Raketmotorer.
N7917020

Publication Date	1978
Personal Author	Nilsson, B.; Sanden, R.
Page Count	31
Abstract	Small amounts of various composite powders containing 85 and 86% perchlorate of ammonium and with HTPB types R-45HT, R-45M, and CS-15 as fuel bonding substance were manufactured. Three different alifact diisocyanates (DDI 1410, IPDI, and TMDI) were used as hardeners. No particular difference between the three hardeners in respect to drag resistance of the powders was noted. In a corresponding comparison between the three HTPB-types, no significant difference was noted between R-45HT and R-45M, whereas better values were obtained at room temperature with CS-15 as bonding substance. At 50 C the stretching of the CS-15 powders amounts to only a few percent due to the high gas conversion temperature of this polymer. Working time for the powder masses is approximately 4 hrs at 53 C with R-45HT or R-45M as bonding substance and DDI as hardener. Experiments were carried out to manufacture materials that could be used as a bonding layer between HTPB powder and rocket engines shell. Materials with good resistance and adherence to both powder and blasted, primer treated steel plate were developed. Of these materials, the bonding part is based on R-45HT and carbon black is the main filler. They are DDI hardened.
Keywords	Composite propellants Hydroxyl compounds Polybutadiene Propellant binders Propellant chemistry Solid propellant rocket engines Ammonium perchlorates Carbon Diisocyanates Hardening(Materials) Solid rocket propellants Hydroxyl terminated polybutadiene Sweden
Source Agency	NASA Foreign Exchange Program
NTIS Subject Category	81H - Rocket Propellants
Corporate Authors	Research Inst. of National Defence, Stockholm (Sweden).
Supplemental Notes	Test in Swedish.
Document Type	Technical Report
NTIS Issue Number	197912