This paper presents the results of investigations into the use of 56 nm nano iron(III) oxide as a combustion rate modifier in a solid heterogeneous rocket propellant (SHRP). A series of solid heterogeneous rocket propellants based on HTPB and ammonium perchlorate with different nano iron(III) oxide contents in the propellant composition were prepared and investigated. The ballistic parameters of the examined propellants were determined by combustion in a laboratory rocket motor (LRM). The ballistic properties were evaluated in the pressure range 5-10 MPa. It was found that the linear burning rate at 7 MPa was increased by 15% for 1% nano iron(III) oxide content in comparison to 0.2% content. Determination of the sensitivity to friction and impact, the calorific value, hardness and decomposition temperature of the derived propellants were also investigated.

This paper presents results from the application of [Cu(TNBI) (NH3)2(H2O)] (CuTNO) to heterogeneous solid rocket propellants based on HTPB/AP, replacing RDX. A series of different compositions of solid heterogeneous rocket propellants based on HTPB and ammonium perchlorate, containing CuTNO or RDX, were prepared and investigated. The ballistic parameters of the examined propellants were determined by combustion in a laboratory rocket motor (LRM). The ballistic properties were evaluated in the pressure range 4-10 MPa and it was found that the linear burning rate at 10 MPa increased by more than 20% for the CuTNO containing propellant, compared to the RDX-based composition. By linear regression of the r = f(p) curves obtained, the burning laws for the investigated propellants were determined. It was found that the CuTNO additive increases the pressure coefficient by over 46%, compared to unmodified propellant. The determination of the sensitivities to friction and impact, the calorific value, hardness and decomposition temperature of the propellants obtained were also investigated.

Streszczenie: W pracy przedstawiono wyniki badań wybranych właściwości stałego heterogenicznego paliwa rakietowego (SHPR) na bazie kauczuku HTPB zawierającego Butacen WprowadzenieTechnologia stałych heterogenicznych paliw rakietowych w znacznej większości przypadków opiera się na zastosowaniu "klasycznego" układu paliwowego w którego skład wchodzą syntetyczny kauczuk HTPB jako główny składnik lepiszcza, adypinian dioktylu (ADO) jako plastyfikator, chloran(VII) amonu (NA) jako utleniacz oraz pył aluminiowy (Al) jako składnik palny [1]. Zgodnie z literaturą prowadzone są prace nad nowymi energetycznymi składnikami lepiszcza takimi jak GAP czy poliNIMMO [2], jednakże wspomniany układ paliwowy na bazie kauczuku HTPB w dalszym ciągu jest poddawany modyfikacjom ze względu na szeroką kompatybilność HTPB ze stosowanymi w SHPR surowcami oraz dobre parametry mechaniczne paliw uzyskiwanych w tym układzie. Spośród powyższych modyfikacji można wyróżnić podstawowe grupy

Solid heterogeneous rocket propellants (SHRP) containing ammonium perchlorate (AP) emit a lot of hydrogen chloride (HCl) during combustion, which poses various environmental issues and makes the detection of the rockets easier. Part of the AP can be replaced by ammonium nitrate (V) (AN), which does not lead to the production of HCl. AN is a commonly used environmentally friendly oxidizer, but it is not usually applied in SHRP due to its disadvantages. One of these disadvantages is a phase transition near room temperature, which causes the density change of AN. Three types of phase stabilized ammonium nitrate (V) (PSAN) with inorganic potassium salts were obtained in order to shift this transition into higher temperatures (above the temperature range of the storage and the usage of SHRP). The SHRP with the PSAN were obtained, and the measurements of the heat of combustion, density, hardness, the sensitivity to mechanical stimuli and the thermomechanical properties were performed. The obtained propellants were characterized by similar operational parameters or were slightly lower than those without the PSAN. This means that AP can be partially replaced without significantly compromising the handling, safety or functionality of the propellants, while increasing the environmental performance of the solution.