Cyanoborohydride (CBH)-based hypergolic coordination compounds for versatile fuels

Energetic transition metal complexes based on 1‐allylimidazole and nitrocyanamide: Syntheses, characterizations and catalytic performances on the thermal decomposition of ammonium perchlorate

“…Constructing energetic coordination compounds with imidazole as the ligand and combining them with metal ions and anions has great application potential [18][19]. Liang et al synthesized four new energetic coordination compounds with copper as the central metal cation, cyanoborohydride as the anion, and different imidazoles as the ligands, all of which showed promoting effects on the thermal decomposition of AP, further demonstrating the great potential of energetic coordination compounds [20]. In addition, Zhong et al synthesized a new energetic coordination compound [Cu(MIM) 2 (AIM) 2 ] (DCA) 2 with 1-methylimidazole (MIM), 1-allyl-imidazole (AIM), copper nitrate, and sodium dicyanamide (NaDCA) as starting materials [21].…”

Energetic isostructural metal imidazolate frameworks with a bridging dicyanamide linker towards high-performance hypergolic fuels

“…Hypergolic propellants are an important type of energetic materials, which are indispensable components of bipropellant systems. [1][2][3][4][5][6] Currently, the most widely used hypergolic fuels are hydrazine and its derivatives monomethylhydrazine (MMH) and unsymmetrical dimethylhydrazine (UDMH) due to their high specific impulse (I sp ) and stable combustion properties. However, these compounds still suffer from many drawbacks including high fuel evaporation pressure, costly transportation and storage techniques, and high toxicity and corrosivity.…”

Metal–organic frameworks as hypergolic additives for hybrid rockets

“…Consequently, chemical propulsion is still the choice for rocket launchers or in-orbit maneuvering, 9,10 with hybrid engines an attractive alternative to complex, and therefore more costly, liquid-fueled engines. 11 To replace polluting propellants and enable competitive small-scale launchers, new technologies [12][13][14][15][16][17][18][19][20][21][22][23][24][25][26][27][28][29] should match or exceed the performance metrics of currently used propulsion approaches. For instance, the characteristic velocity (C*) is a measure of the combustion performance of a rocket propulsion system, independent of its nozzle.…”