Results 141 to 150 of about 410 (183)

Flame structure of ADN/HTPB composite propellants

Combustion and Flame, 2001
Abstract Visual flame characteristics, burning rates, and final flame temperatures for propellants based on ammonium dinitramide (ADN) and hydroxyl-terminated polybutadiene (HTPB) at different HTPB concentrations (3–20%) have been studied at pressures of 0.05 to 0.6 MPa.
Oleg P Korobeinichev, Alexander A Paletsky   +1 more
openaire   +1 more source

Oscillatory combustion of fine-AP/HTPB propellants

36th AIAA Aerospace Sciences Meeting and Exhibit, 1998
The steady and oscillatory combustion of wide distribution AP/HTPB composite propellants containing coarse AP and fuel-rich, fine-AP/HTPB pocket regions is being investigated experimentally and theoretically. These propellants are of special interest because they are similar to many wide distribution bi-modal tailorable plateau propellants.
S. Hickman, M. Brewster
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

HTPB‐based polyurethanes for inhibition of composite propellants

Journal of Applied Polymer Science, 1995
AbstractPolyurethanes were synthesized by the reaction of hydroxyterminated polybutadiene (HTPB) and diisocyanates such as toluene diisocyanate (TDI), diphenylmethane diisocyanate (MDI), hexamethylene diisocyanate (HMDI), and isophoron diisocyanate (IPDI).
D. C. Gupta, S. S. Deo, D. V. Wast, S. S. Raomore, D. H. Gholap   +4 more
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

Tensile fracture of HTPB based propellant specimens

Materials Science and Technology, 2002
AbstractThe failure of a viscoelastic material, such as solid propellant, is a complex phenomenon with a requirement to address the following two fundamental and complementary aspects in the failure criteria. First, what is the failure criterion for a solid propellant in stress–strain space, and what are the variations in failure data when failure is ...
K. Renganathan, B. S. V. Rama Sarma, B. Nageswara Rao, M. K. Jana   +3 more
openaire   +1 more source

Development of AP/HTPB based Fuel-rich Propellant for Solid Propellant Ramjet

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, 2013
It is well known that reduction of Ammonium Perchlorate (AP) content in composite propellant reduces the burn rate of solid composite propellants. Below a certain level of AP content the propellant does not burn. This paper explores ways to enhance the burn rate of fuel-rich composite solid propellant.
jogesh K. nanda, P. A. Ramakrishna
openaire   +1 more source

Critical impact initiation energies for three HTPB propellants

26th Joint Propulsion Conference, 1990
The instrumented drop weight impact machine is one possible candidate for establishing the hazard response of solid rocket propellants to impact. The plastic work done on the propellant prior to initiation can be measured by equating it to the loss in drop weight kinetic energy, provided energy storage in the machine is negligible.
P. J. Baker, A. M. Mellor, C. S. Coffey
openaire   +1 more source

Emission imaging of AP/HTPB propellant sandwich combustion

Combustion Science and Technology, 2002
Ultraviolet emission imaging (305-315 nm) was used to study the combustion of sandwiches of ammonium perchlorate (AP) and hydroxyl-terminated polybutadiene (HTPB) in nitrogen at pressures up to 32 atm, with binder layers from 50 to 450 µm in thickness.
B. T. Chorpening, M. Q. Brewster
openaire   +1 more source

The Damage Law of HTPB Propellant under Thermomechanical Loading

Journal of Energetic Materials, 2015
By way of measuring the acoustic emission (AE) signals of Hydroxyl-terminated polybutadiene (HTPB) propellant in condition of uniform speed, and combined with the scanning electron microscopy (SEM) fracture surface observation, the damage law of HTPB composite solid propellant under thermomechanical loading was studied.
Cheng-wu Liu, Jian-hong Yang, Xian-meng Wang, Yong-kang Ma   +3 more
openaire   +1 more source