Energiereiche feste Brennstoffe fur Feststauraketen (111) Feststauraketen operieren durch Verbrennung eines brennstoffreichen Gases, erzeugt in einer Primarbrennkammer, mit verdichteter Luft, die aus der Atmosphare in eine Sekundarbrennkammer eingefuhrt wird. Somit hangt die Brennleistung ab vom Misch-und Reaktionsverlauf des brennstoffreichen Gases und vom Luftstrom in der Sekund&kammer. Die Festbrennstoffe, die in dieser Arbeit untersucht wurden, bestanden aus Composittreibstoffen auf Basis Ammoniumperchlorat mit Zusatz von Borpartikeln. Die Verbrennungseffizienz der Borpartikel in der Sekundarbrennkammer wurde bestimmt als Funktion der Luftzumischung und des Luft/Brennstoff-Verh%ltnisses. Zwei Arten der Luftzufiihrung wurden angewandt zur Auswertung der Verbrennung der Borpartikel. Brennversuche, vorgenommen bei festverbundener Luftzufuhrung, zeigten, daR die Verbrennungseffizienz signifikant zunahm, wenn ein MehrfacheinlaR verwendet wurde, bestehend aus zwei vorderen und zwei hinteren Einldoffnungen. Combustibles solides energktiques pour stato-fusees (111)Les stato-fusbes opbrant par combustion d u n gaz riche en combustible, gtntrt dans un chambre de combustion primaire, avec de l'air cornprime provenant de l'atmosphere, qui est introduit dans une chambre de combustion secondaire. La performance de combustion dtpend donc des processus de mClange et de rCaction du gaz riche en combustible et de I'Ccoulement dair dans la chambre de combustion secondaire. Les combustibles solides CnergCtiques examints dans cette ttude ttaient composts de combustibles composites B base de perchlorate d'ammonium avec addition de particules de bore. L'efficacitB de combustion des particules de bore dans la chambre de combustion secondaire a Ctt dtterminte comme une fonction du mtlange dair et du rapport air/combustible. On a utilisC deux modes dalimentation dair pour Cvaluer la combustion des particules de bore. Les essais de combustion effectuts avec une alimentation d'air directe ont montrt que l'efficacitt de combustion augmentait de manitre significative lorsqu'on utilisait une admission multiple composke de deux orifices dadmission ii l'avant et de deux autres B I'arribre. SummaryDucted rockets operate with the combustion of fuel-rich gas generated in a primary combustor and the ram-air induced from the atmosphere to a secondary combustor. Thus, the combustion performance depends on the mixing and reaction processes of the fuel-rich gas and the air flow in the secondary combustor. The energetic solid fuels examined in this study consisted of ammonium perchlorate based composite propellants containing boron particles. The combustion efficiency of boron particles in the secondary combustor was determined as a function of air-mixing process and airlfuel ratio. Two types of air-inlet were used to evaluate the combustion of boron particles. Combustion tests conducted by direct connect flow indicate that the combustion efficiency increased significantly when a multi-port consisting of two forward-ports and two rear-ports was used.
Ducted rockets operate with the combustion of fuel‐rich gas generated in a primary combustor and the ram‐air induced from the atmosphere to a secondary combustor. Thus, the combustion performance depends on the mixing and reaction processes of the fuel‐rich gas and the air flow in the secondary combustor. The energetic solid fuels examined in this study consisted of ammonium perchlorate based composite propellants containing boron particles. The combustion efficiency of boron particles in the secondary combustor was determined as a function of air‐mixing process and air/fuel ratio. Two types of air‐inlet were used to evaluate the combustion of boron particles. Combustion tests conducted by direct connect flow indicate that the combustion efficiency increased significantly when a multi‐port consisting of two forward‐ports and two rear‐ports was used.
Struktur der Verbrennungswelle yon Ammoniumperchlorat-Composit-TreibstoffenDer Abbrandmechanismus von AP-Composit-Treibstoffen wurde untersucht. Die oxydatorreichen Treibstoffe wrurden erhalten durch einen UberschuR an AP-Anteilen. Die Druckgrenze der Deflagration des Treibstoffs nimmt ab mit zunehmender Konzentration des Binders. Die Verbrennungswelle besteht aus zwei Reaktionszonen I und 11: Zone I ist der Bereich der AP-Flamme und Zone I1 der Bereich der Diffusionsflamme. Der Warmeflu8 von der Gasphase zur Abbrandoberflache nimmt zu mit zunehmendem Druck, der WarmefluR ist verantwortlich fur die Charakteristik der Abbrandgeschwindigkeit. Structure de l'onde de combustion des propergols composites a base de perchlorate d'ammoniumOn a ktudit le mtcanisme de combustion de propergols composites A base de perchlorate d'arnmonium. Les compositions riches en comburant ttaient rtalistes par une teneur exctdentaire en perchlorate d'ammonium. Le seuil de pression a partir duquel se produit une dtflagration, se trouve abaissk lorsque la concentration en liant augmente. L'onde de combustion comporte deux zones de rtaction: la zone I correspond a la flamme du perchlorate d'ammonium, la zone I1A la flamme diffuse. Lorsque la pression croit, le flux de chaleur de la phase gazeuse vers la surface en combustion augmente et c'est ce flux de chaleur qui determine la vitesse de combustion. SummaryThe combustion mechanism of ammonium perchlorate (AP) composite propellants were studied. The oxidizer-rich propellants tested were made with excess concentrations of AP particles. The pressure deflagration limit of propellant decreases with increasing the concentration of binder. The combustion wave consists of two reaction regions I and 11: the region I is the zone of AP monopropellant flame and the region I1 is the zone of diffusion flame. The heat flux feedback from the gas phase to the burning surface increases as pressure increases, and the heat flux is responsible for the burning rate characteristics.
The buring rate of ammonium perchlorate (AP) composite propellants is decreased significantly by the addition of SrCO3 without increasing the pressure exponent of burning rate. Results of microthermocouple measurements indicate that the burning surface temperature is increased from 700 K to 970 K by the addition of SrCO3, although the heat release rate in the gas phase is remained unchanged. DTA (differential thermal analysis) and TG (thermogravimetry) experiments were also carried out in order to determine the role of SrCO3 in the decomposition process of AP. The AP decomposition temperature is increased from 590 K to 620 K by the addition of SrCO3. The results of analysis show that the reduction of the burning rate is caused by the increased AP decomposition temperature.
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