Examination of AP/KN composite propellant thermal wave structure under steady-state burning
Апстракт
A formulation of composite propellant based on modified PVC binder has been produced, such that part of the ammonium perchlorate has been replaced with potassium nitrate. This resulted in improved environment behavior at the expense of unusual changes in burning rate at different pressures, with alarmingly high-pressure exponent during burning at pressures over 2 MPa. The aim of this investigation is to examine processes in the combustion wave near the burning surface during combustion. A technique based on fine-wire thermocouples embedded in the propellant has been used to accomplish precision measurement of temperature profiles through the entire flame zone of the solid propellants. This paper reports the technique and measurement results.
Кључне речи:
Microthermocouple technique / AP/KN composite rocket propellantИзвор:
Advancements in Energetic Materials and Chemical Propulsion, 2005, 195-210Scopus: 2-s2.0-84874750536
Колекције
Институција/група
Mašinski fakultetTY - CONF AU - Bozić, V.S. AU - Miloš, Marko AU - Blagojević, Đorđe AU - Jankovski, B.S. PY - 2005 UR - https://machinery.mas.bg.ac.rs/handle/123456789/547 AB - A formulation of composite propellant based on modified PVC binder has been produced, such that part of the ammonium perchlorate has been replaced with potassium nitrate. This resulted in improved environment behavior at the expense of unusual changes in burning rate at different pressures, with alarmingly high-pressure exponent during burning at pressures over 2 MPa. The aim of this investigation is to examine processes in the combustion wave near the burning surface during combustion. A technique based on fine-wire thermocouples embedded in the propellant has been used to accomplish precision measurement of temperature profiles through the entire flame zone of the solid propellants. This paper reports the technique and measurement results. C3 - Advancements in Energetic Materials and Chemical Propulsion T1 - Examination of AP/KN composite propellant thermal wave structure under steady-state burning EP - 210 SP - 195 UR - https://hdl.handle.net/21.15107/rcub_machinery_547 ER -
@conference{ author = "Bozić, V.S. and Miloš, Marko and Blagojević, Đorđe and Jankovski, B.S.", year = "2005", abstract = "A formulation of composite propellant based on modified PVC binder has been produced, such that part of the ammonium perchlorate has been replaced with potassium nitrate. This resulted in improved environment behavior at the expense of unusual changes in burning rate at different pressures, with alarmingly high-pressure exponent during burning at pressures over 2 MPa. The aim of this investigation is to examine processes in the combustion wave near the burning surface during combustion. A technique based on fine-wire thermocouples embedded in the propellant has been used to accomplish precision measurement of temperature profiles through the entire flame zone of the solid propellants. This paper reports the technique and measurement results.", journal = "Advancements in Energetic Materials and Chemical Propulsion", title = "Examination of AP/KN composite propellant thermal wave structure under steady-state burning", pages = "210-195", url = "https://hdl.handle.net/21.15107/rcub_machinery_547" }
Bozić, V.S., Miloš, M., Blagojević, Đ.,& Jankovski, B.S.. (2005). Examination of AP/KN composite propellant thermal wave structure under steady-state burning. in Advancements in Energetic Materials and Chemical Propulsion, 195-210. https://hdl.handle.net/21.15107/rcub_machinery_547
Bozić V, Miloš M, Blagojević Đ, Jankovski B. Examination of AP/KN composite propellant thermal wave structure under steady-state burning. in Advancements in Energetic Materials and Chemical Propulsion. 2005;:195-210. https://hdl.handle.net/21.15107/rcub_machinery_547 .
Bozić, V.S., Miloš, Marko, Blagojević, Đorđe, Jankovski, B.S., "Examination of AP/KN composite propellant thermal wave structure under steady-state burning" in Advancements in Energetic Materials and Chemical Propulsion (2005):195-210, https://hdl.handle.net/21.15107/rcub_machinery_547 .