Results 181 to 190 of about 2,333 (214)

A Study of a Novel Additive for HTPB Propellant

1976
Abstract : Experimental studies were conducted to define the utility regimes of graphite linters (chopped graphite fiber ranging from 50 to 200 micrometers) with respect to burn rate augmentation, acoustic stabilization and processing improvement in HTPB composite propellant. Linter utility regimes were defined with respect to burn rate reproducibility
M. W. Beckstead, A. G. Butcher, J. P. Peterson   +2 more
openaire   +1 more source

Development of a N2O/HTPB hybrid rocket motor

33rd Joint Propulsion Conference and Exhibit, 1997
Experiments were performed as a part of the Hybrid Propulsion Demonstration Program (HPDP) in order to demonstrate a N2O/HTPB hybrid sounding rocket. Multiple hybrid motors have been tested at Environmental Aeroscience Corporation in order to develop a high performance hybrid flight system.
J. Arves, H. Jones, K. Kline, K. Smith, Ted Slack, T. Bales, J. Arves, H. Jones, K. Kline, K. Smith, Ted Slack, T. Bales   +11 more
openaire   +1 more source

Development of HTPB Propellant for Ballistic Missiles

1974
Abstract : The program objective is to develop a family of solid propellants for ballistic missiles based on an HTPB (hydroxyl terminated polybutadiene) binder, and to demonstrate one optimized propellant formulation by large scale motor firings. Specifically, five propellants have been formulated and are being characterized to the point that they will
Even E. Day, Grant Thompson
openaire   +1 more source

Chemistry and kinetics of hydroxyl-terminated polybutadiene (HTPB) and diisocyanate-HTPB polymers during slow decomposition and combustion-like conditions

Combustion and Flame, 1991
Abstract The decomposition chemistry and kinetics of hydroxyl-terminated polybutadiene (HTPB), hydroxyl-terminated polyethyleneglycol adipate (HTPA), and diisocyanate cross-linked HTPB (diisocyanates = TDI, IPDI, and DDI) were determined by TGA, DSC, and IR spectroscopy at 10°C/min and by SMATCH/FTIR at 250°–350°C/s. At 10°C/min, the first step (300°–
J.K. Chen, T.B. Brill
openaire   +1 more source

ADN Recrystallization and Microencapsulation with HTPB by Simple Coacervation

Propellants, Explosives, Pyrotechnics, 2020
AbstractAmmonium dinitramide (ADN) has been considered the potential substitute for ammonium perchlorate in solid green propellants. However, it has also some drawbacks due to its high hygroscopicity and chemical incompatibility with some of the components present in composite propellant formulations.
Jessica de Oliveira Silva, Kamila Pereira Cardoso, Josiane Ribeiro Campos Silva, Elizabete Yoshie Kawachi, Márcio Yuji Nagamachi, Luiz Fernando de Araujo Ferrão   +5 more
openaire   +1 more source

Droplet Impact of Additives and HTPB

AIAA SCITECH 2023 Forum, 2023
Marc A. Magana, Alexander Klotz, Joseph Kalman   +2 more
openaire   +1 more source

Evaluation of tg data of htpb-based polyurethanes

Journal of Thermal Analysis and Calorimetry, 2004
Thermogravimetry (TG) was used to provide some new information on some polybutadiene-based polyurethanes. The results showed two main mass decomposition stages, from 230 to 564°C. The first mass loss stages were used to quantify the hard segments of the polymers. The results correlated well with the ASTM methodology.
E. F. S. Vieira, A. R Cestari, S. F. Zawadzki, S. M. Rocha   +3 more
openaire   +1 more source

HTPB Combustion Temperature Measurements

AIAA SCITECH 2023 Forum, 2023
Clayton M. Geipel, Christopher J. Pfutzner, Brian T. Fisher   +2 more
openaire   +1 more source

HTPB-based polyurethanes. II. SINs with PMMA

Journal of Polymer Science Part B: Polymer Physics, 2000
Simultaneous interpenetrating networks from poly(methyl methacrylate-co-ethyleneglycol dimethacrylate) (PA) and a hydroxyl-terminated polybutadiene-based polyurethane (PU) were prepared with various hard-segment contents (X) in the PU and different ratios (PU/PA) between the components. The level of the reinforcement, the mechanism of molecular failure,
S. H. Wang, S. Zawadzki, L. Akcelrud
openaire   +1 more source

Aluminum agglomeration of AP/HTPB composite propellant

Acta Astronautica, 2019
Abstract Aluminum (Al) powder agglomeration is one of the main reasons for the degradation in the performance of aluminized solid propellant rockets and so, understanding the combustion behavior of aluminum in solid propellants is of great importance.
Jifei Yuan, Jianzhong Liu, Yunan Zhou, Jianru Wang, Tuanwei Xv   +4 more
openaire   +1 more source