An entry from the Cambridge Structural Database, the world’s repository for small molecule crystal structures. The entry contains experimental data from a crystal diffraction study. The deposited dataset for this entry is freely available from the CCDC and typically includes 3D coordinates, cell parameters, space group, experimental conditions and quality measures.

One of the ways of solving the problem of reducing the man-made impact of rocket and space activities on the environment, based on the reduction of the impact areas of separating launch vehicle component (LVC) in the process of launching payloads into orbit are considered. Known particular solutions to this problem, for example, the return of spent LV stage accelerators to the point of launch, a multiple reduction in the impact areas of spent LV stage accelerators due to their controlled descent, however, there is open the question of how to deal with such LVC as payload fairings (PF) and aft-interstage (AIS) having significant areas of the impact areas. The possibility of burning LVC, such as PF and AIS, made of a composite material based on carbon fiber is considered. The thermal conditions of LVC during their movement on the descent path are investigated, the necessary amount of heat for heating the LVC to the ignition temperature is determined and various options of energy materials (EM) are considered. On the example of a typical PF, having a design of a polymer composite material (carbon fiber) with an aluminum honeycomb core (AHC), another structure is proposed, where a filler based on a mixture of polymer films such as ABS structure and energy material is used instead of AHC. The proposed design of the polymer composite material allows to provide the necessary operation parameters of the PF (strength, thermal protection, etc.) at the stage of preparation of the PF for a launch, LV ascent in the active section of the trajectory. And the possibility of burning after the mission with minimal energy costs allows to provide.

This paper considers the effects of binder mass fraction on the properties of energetic formulations based on zirconium and zirconium hydride. These ingredients, replacing aluminum in solid rocket motors with low vehicle performance coefficient, may increase the propellant ballistic effectiveness, thanks to the resulting higher density and notwithstanding their lower specific impulse. The propellant ballistic effectiveness is estimated via the vehicle velocity achieved using the propellant under analysis in a real vehicle. For each specific mission, the binder content can be varied to provide the optimal relationship between energetic and physical-mechanical properties, that is, one may sacrifice energy in favor of rheological and physicomechanical properties (increasing binder mass fraction), or vice versa .

The investigation considers phase stabilization of ammonium nitrate for considerable extension of its application area including new generation of gas-generating compositions for airbag inflators. It was shown that alloys of ammonium nitrate with small amounts (2-10%) of some organic compounds can have no phase transitions or at least have only one instead of three ones in initial ammonium nitrate. The mostly effective as stabilizers are the compounds that have rather close crystallographic parameters. A strong donor-acceptor interaction between nitrate-anion and organic molecules are found. Using quantum-chemical calculations, X-ray analysis, X-ray phase analysis, UVand IR-spectroscopy it was found a new ammonium nitrate phase state in its alloy with some organic additives. This state is stable in temperature range between -50 and +100 °C.