Review: 47 refs.

Histone deacetylases (HDACs) are overexpressed in various types of primary human cancer and have become attractive targets for cancer therapy. We designed and synthesized a series of new class of HDAC inhibitors (HDACi). Among these, S-(E)-3-(1-(1-(benzo[d]oxazol-2-yl)-2-methylpropyl)-1H-1,2,3-triazol-4-yl)-N-hydroxyacrylamide (NK-HDAC-1) showed potent antitumor activity. In the present study, we examined the antitumor effects of NK-HDAC-1 on breast cancer in vitro and in vivo. The inhibitory effects of NK-HDAC-1 on HDAC enzyme activity and cell growth were more potent compared to suberoylanilide hydroxamic acid (SAHA). NK-HDAC-1 caused G1 cell cycle arrest at concentrations below 0.2 µM and G2/M arrest at concentrations above 0.4 µM through p21 upregulation and cyclin D1 downregulation. NK-HADC-1 induced hyperacetylation of histone H3 and H4 around the promoter region of p21. NK-HDAC-1 promoted apoptosis in MDA-MB-231 breast cancer cells by activating both the intrinsic and the extrinsic pathway NK-HDAC-1 at doses of 3, 10 and 30 mg/kg reduced the tumor volume in MDA-MB-231 xenografts by 25.9, 48.8 and 63.6%, respectively. The results suggested that NK-HDAC-1 may be a promising therapeutic candidate in treating human breast cancer.

ADN/water‐based gel propellant is a new high‐energy, green, non‐toxic propellant, so it has good application prospects in the future aerospace industry. In order to study the spray characteristics of ADN/water‐based gel propellant, two‐strand impinging nozzles were used to carry out experiments. The spray images were observed by high‐speed photography, and the effects of different injection pressure, nozzle diameter, and impact angle on spray configuration, spray cone angle and breakup length of liquid film were studied. The results show that the breakup length of liquid film decreased with the increase in injection pressure and impact angle, and increased with the increase in nozzle diameter. The spray cone angle increased with the increase in injection pressure, nozzle diameter, and impact angle. And the effects of spray pressure and nozzle diameter on spray process were obvious. The distribution of propellant spray in space was clarified under these conditions and it would provide reference data for the structural design of the combustion chamber of the engine.